Abstract: A primary support strut structure and a method of manufacturing thereof for an aircraft power plant is disclosed having a first half-shell including a first free edge, and a second half-shell having a second free edge. The first half-shell and the second half-shell are assembled together by joining the first free edge and the second free edge so as to form a box-shaped structure. The two half-shell construction results in very rigid box structure, and a reduced number of ribs in the primary structure.

Abstract: An engine assembly with an electric motor that includes a cooling system of which a heat sink portion is arranged in an exhaust cone downstream of the fan driven by the electric motor, that is designed to effect thermal exchanges with a wall of the exhaust cone. Such an electric rear fan arrangement with boundary layer ingestion enables a cold air flow coming from the fan when the engine assembly is in operation to be used to cool the different components of the engine assembly.

Abstract: To allow the attachment of an engine of the “Open Rotor Puller” type to the rigid structure of an attachment pylon, an attachment structure comprises a first attachment structure shifted forwards with respect to the center of gravity of the engine and connected to the rigid structure through a pyramid, a second attachment structure laid out at the rear with respect to the first attachment structure and extending in a plane of a first stringer of the rigid structure, and a third attachment structure laid out at the rear with respect to the second attachment structure. The second attachment structure comprises two engine attachments for recovering the moment along the axis of the engine, laid out on either side of a horizontal symmetry plane of the engine.

Abstract: In order to simplify the design of an aircraft turbo engine propeller while enhancing the safety function thereof related to control of the blade angle of attack, a propeller is provided comprising a secondary rotational coupling to couple in rotation, along the radial axis of the blade, the inner radial end of the blade root with a mechanical joining member of a blade angle of attack control device, the secondary coupling being designed and configured to be active in the event of failure of the main pin.

Abstract: To reduce the overall mass of an engine assembly for aircraft, this assembly comprises a part of the fuselage of an aircraft, a turbomachine comprising an unfaired propeller, together with an annular row of unfaired after-guide vanes located aft of the propeller and rotationally fixed in relation to a longitudinal axis of the turbomachine, and a mounting pylon. At least part of the leading edge of the pylon is incorporated within the annular row between two after-guide vanes.

Abstract: A thrust reverser system with a thrust reverser cascade and a reverser door with door segments laid out in a folded condition relatively to each other in an inactive configuration of the reverser system, and accommodated in an accommodation space located outside the secondary channel. Upon passing from the inactive configuration to the active configuration a rearward displacement of the cascade towards a nacelle aperture, released by an external movable nacelle cowl driven rearwards by the cascade, and a deployment of segments until they attain a deployed closing position within the secondary channel occurs simultaneously.

Abstract: A propeller propulsion unit, comprising at least one kinematic system comprising at least: a heat engine, an electrical energy generator, an electric motor configured to generate a rotary movement as output from the electrical energy generated by the electrical energy generator, a drive and selection device configured to assume a first configuration, in which it is coupled to the output of the electric motor, and a second configuration, in which it is coupled to the main shaft of the heat engine, and a propeller rotated by the drive and selection device. Such a propeller propulsion unit with a hybrid engine allows more power to be provided and facilitates maintenance and ergonomics and is safer.

Abstract: An aircraft power unit is disclosed having an engine, which an output shaft linked to a driveshaft of a fan positioned downstream of the engine. The fan is included in a duct formed by a nacelle of the power unit. The nacelle is linked to the driveshaft of the fan by a nacelle pivot formed downstream of the fan.

Abstract: A primary structure of a strut for bearing an aircraft power plant including a front part intended to be joined to an aircraft power plant and a rear part intended to be joined to a structure of the aircraft, the front part being formed from a box including an upper longitudinal member, a lower longitudinal member, and lateral panels. A main rib is located at an interface between the front part and the rear part. The rear part is formed from a set of four connecting rods. The first end of each connecting rod is joined to the front part of the primary structure and the second end of each connecting rod is joined to a separate interface for fastening to the structure of the aircraft. This allows a substantial simplification of the primary structure of a strut for bearing an aircraft power plant, which can have advantages in particular in terms of cost, mass, and simplicity of implementation and integration.

Abstract: An assembly for an aircraft and comprising a wing comprising an airfoil box partly produced using a front spar, a mounting pylon arranged under the wing and comprising a primary structure formed as a primary box having a top spar extending at least partly under the airfoil box and having a slit, a bottom spar, lateral panels and a transverse reinforcing fixing rib, of which a bottom part is housed and fixed inside the primary structure and of which a top part passes through the slit. A fixing arrangement fixes the top part to the front spar. The fixing arrangement comprises a plurality of fixing bolts, where each fixing bolt fixes the top part to the front spar and has its axis at right angles to the fixing rib. Such an assembly allows the mounting pylon primary structure to be as close as possible to the wing.

Abstract: An aircraft comprises a wing, an engine attachment pylon comprising a primary structure and an arrangement for securing the primary structure to a wing box. This arrangement comprises two lateral front fittings, each of these fittings comprising a first connecting portion secured to the front wing spar, a second connecting portion secured to the primary structure, at least one securing member articulated to each of the first and second connecting portions. Furthermore, the first connecting portions of the two fittings are made in one piece in a single wing connector extending over essentially the entire height of the front wing spar.

Abstract: An aircraft comprising a wing, an engine attachment pylon comprising a primary structure and an arrangement for securing the primary structure to a wing box. The arrangement comprises two lateral front fittings, each of these fittings comprising a first connecting portion secured to the front wing spar, a second connecting portion secured to the primary structure of the attachment pylon, at least one securing member linking the first and second connecting portions, this securing member being articulated to the first connecting portion with the aid of a first pin system oriented substantially parallel to the front wing spar.

Abstract: In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.

Abstract: A device for manipulating a hollow shaft configured to create a pivot link between a first element and a second element. The manipulation device comprises a cylindrical body having a diameter variable by radial contraction or radial expansion of the cylindrical body, a module for controlling the diameter of the cylindrical body configured so that the diameter of the cylindrical body has alternatively at least a first diameter suitable for the cylindrical body to be displaced in the hollow shaft and a second diameter suitable for the cylindrical body to be blocked in the hollow shaft. The cylindrical body comprises an end configured to protrude from the hollow shaft when the cylindrical body is blocked in the hollow shaft. The manipulation device allows the alignment of the orifices due to the end configuration of the cylindrical body.

Abstract: An aircraft which comprises a fuselage and at least one propulsion assembly linked to the fuselage by at least two connecting rods positioned at least partially in an inner zone of the air inlet of the nacelle of the propulsion assembly. Thus, the connecting rods do not interfere with the secondary flow flowing inside the nacelle and do not affect the aerodynamic performance levels of the propulsion assembly.

Abstract: A primary support strut structure and a method of manufacturing thereof for an aircraft power plant is disclosed having a first half-shell including a first free edge, and a second half-shell having a second free edge. The first half-shell and the second half-shell are assembled together by joining the first free edge and the second free edge so as to form a box-shaped structure. The two half-shell construction results in very rigid box structure, and a reduced number of ribs in the primary structure.

Abstract: A primary structure of an aircraft power plant support pylon is disclosed having a bottom stringer and two lateral walls formed in a single piece or welded so as to form a U-shaped bottom part, and a top cover which closes the U-shaped bottom part. The U-shaped part closed by a cover makes it possible to construct a box or box structure that exhibits a rigidity suitable for taking up the forces deriving from the power plant and makes it possible to limit the number of ribs (C1 . . . C10) in the structure.

Abstract: In order to reduce the risks of movable nacelle cowlings opening, the invention provides a nacelle for an aircraft engine assembly comprising a fixed nacelle structure as well as at least one jointed movable cowling on the fixed structure, the cowling being jointed at its front end on the fixed structure so that, upon closing the movable cowling, a rear end of this cowling moves towards the rear and radially towards the inside.

Abstract: A nacelle having a longitudinal axis and comprising a chassis, two articulated fan cowl doors and a sliding fan cowl door. Each articulated fan cowl door is rotatably mounted in an upper portion of the chassis, each about their own opening axis. The opening axes are parallel to the longitudinal axis. The articulated doors pivot between a closed position and an open position. The sliding fan cowl door, in its closed position, is placed between free edges of the articulated fan cowl doors. A sliding arrangement for the sliding door is configured such that, in the open position of either articulated door, the sliding fan cowl door can rotate about the longitudinal axis. The nacelle has fan cowl doors which take up less space when in the open position and which are more compact, in comparison to articulated fan cowl doors without a sliding fan cowl door.

Abstract: An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.