Abstract: A propulsion assembly for an aircraft, comprising a pylon to be secured below a wing of the aircraft and having a front face and a lower face, and a turbomachine comprising, from upstream to downstream in a direction of a flow of air passing through the turbomachine during operation, a fan and an engine driving the fan. The fan is faired by a fan casing and the engine is faired, from upstream to downstream, by an intermediate casing and an engine casing, the intermediate casing having a hub and an outer ring extending the fan casing, the ring being spaced apart radially from the hub and secured to the latter by arms extending in an air duct. The propulsion assembly comprises a front engine attachment secured between the pylon front face and the hub and a rear engine attachment secured between the pylon lower face and the engine casing.

Abstract: A thrust reverser system includes two thrust reversal cascades, of which the first cascade is entrained by an actuator, and which are configured to adopt a retracted position in which they are housed in a space located outside the duct. The action of the actuator brings about: rearward displacement of the first cascade in the direction of a nacelle opening; and during part of the rearward displacement of the second cascade, simultaneous pivoting of this second cascade under the action of a control lever, the interaction of which with a fixed guide rail forces the front end of the lever to move radially inwards while the lever is entrained rearwards by the second cascade.

Abstract: In order to bring the primary structure of an engine mounting pylon of an aircraft as close as possible to a wing box: —an aircraft wing includes a wing box made partly by a front spar and an intermediate spar; —a mounting pylon including a primary structure in the form of a box having transverse reinforcement ribs; and —attachment means for attaching the primary structure of the mounting pylon on the wing box. These attachment means include a row of bolts along which each bolt passes through a structural part of the pylon on one hand, and on the other hand a fitting attached to one of the front and intermediate spars.

Abstract: A joint for connecting a first aircraft structure to a second aircraft structure such that relative rotation and relative translational movement of the first and second aircraft structures along a first axis is permitted, whilst relative translational movement of the first and second aircraft structures along axes orthogonal to the first axis is substantially prevented. The joint includes a bracket having an opening aligned with the first axis; a pin aligned with the first axis and extending through the opening; and a bearing mounted in the opening. The bearing has an inner bearing surface defining a bore through which the pin extends, which is configured for translational sliding contact with the pin, and a part-spherical outer bearing surface configured for rotational sliding contact with the opening.

Abstract: A method for mounting an aircraft pylon connected to a wing includes: a step of pre-positioning first and second contact surfaces respectively provided on the wing and the pylon, a step of installing and tightening temporary connection elements, so as to keep the first and second contact surfaces clamped against one another, a step of installing and expanding at least one radially expandable element in at least one pair of first and second receptacles respectively provided on the wing and the pylon, a step of installing and tightening final connection elements connecting the pylon and the wing in the mounted state, a step of removing the radially expandable element(s) and the temporary connection elements, and of installing the remaining final connection elements and shear pin(s).

Abstract: In order to reduce congestion of attachments between an aircraft engine and its attachments, an engine assembly is provided, the primary structure of the device of which includes a structural cover surrounding the engine and connected on a central box, the cover including an outer skin interiorly delimiting a secondary flow. A group of main mounts is provided as a group of secondary mounts laid out at the rear of the group of main mounts, the group of main mounts including a plurality of bolts distributed around the longitudinal axis of the engine and ensuring the attachment of a front end of the cover to the hub of the intermediate case, and a group of secondary mounts including a plurality of secondary mounts distributed around the axis and ensuring attachment of a rear portion of the engine to a rear end of the cover.

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 turbofan comprising a fan casing and a nacelle comprising a cowl translatable between an advanced position and a pushed-back position in which the mobile cowl and the fan casing define a window therebetween. The nacelle also comprises reverser flaps, each reverser flap being mounted in a linked manner on the mobile assembly between a closed position in which it obstructs the window and an open position in which it does not obstruct the window. The nacelle also has an impelling mechanism comprising a lever arm rotatable on the mobile assembly and having a roller, a connecting rod mounted rotatably between the reverser flap and the lever arm, and a channel receiving the roller, the channel having a front part parallel with the translation direction and a rear part extending after the front part and oriented inward as it progresses from the front toward the rear.

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: In order to reduce the size of the attachment arrangement between an aircraft engine and its attachment device, an engine assembly is provided for which the primary structure of the attachment device includes a central box and two movable structural cowls. Further the arrangement for attaching the engine on the structure comprises a group of main ties laid out in a main transverse plane for absorbing forces crossing a front end of the movable structural cowls, this group comprising three main shearing pins radially oriented and distributed around a longitudinal axis of the engine, each pin crossing a first shearing orifice provided on a fitting secured to the hub of the intermediate case on the one hand, and a second shearing orifice provided on one of the movable cowls or on its connecting structure to the central box on the other hand.

Abstract: To reduce flexural deformations of an engine, an engine assembly comprises a device for attaching the engine onto a structure of an aircraft, the attachment device including a primary structure, an attachment device for attaching the engine onto the primary structure of the attachment pylon, and a nacelle including thrust reversal cowls, each equipped with an inner structure arranged around a case portion of the engine. The assembly includes flexible devices for transmitting forces, arranged between the case portion and the inner structures of the cowls, each device including an elastically deformable device configured so that in the closed position of the cowl, with the engine at a standstill, it adopts a partial elastic deformation state allowing the device to apply a prestress force on the case portion.

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: In order to bring a turbofan engine closer to the lower surface of a wing box, the disclosure herein foresees an assembly for an aircraft including a mount for mounting a rigid structure of an engine strut to the wing box, the mount including an upper wing mount including a fitting secured to the upper surface of the wing box.

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: To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.

Abstract: In order to reduce the width of the attachment between the rear portion of an aircraft engine and its attachment pylon, an engine assembly attachment include an assembly of rear engine attachments comprising a first connecting rod laid out in a longitudinal and median vertical plane, a second connecting rod substantially laid out tangentially to the inter-turbine case, and a rear engine attachment for transversely spreading the loads, axially shifted rearwards relatively to the first and second connecting rods, and comprising a shear pin oriented along a vertical direction of the engine assembly.

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 turbofan comprising a fan casing and a nacelle comprising a cowl translatable between an advanced position and a pushed-back position in which the mobile cowl and the fan casing define a window therebetween. The nacelle also comprises reverser flaps, each reverser flap being mounted in a linked manner on the mobile assembly between a closed position in which it obstructs the window and an open position in which it does not obstruct the window. The nacelle also has an impelling mechanism comprising a lever arm rotatable on the mobile assembly and having a roller, a connecting rod mounted rotatably between the reverser flap and the lever arm, and a channel receiving the roller, the channel having a front part parallel with the translation direction and a rear part extending after the front part and oriented inward as it progresses from the front toward the rear.

Abstract: A thrust reverser system includes a thrust reversal cascade and a reverser door which are accommodated in a housing situated outside a secondary flow duct. The system also includes connection parts the presence of which combined with the action of the actuator gives rise simultaneously to: displacement rearwards of the cascade in the direction of a nacelle opening, cleared by a nacelle cowling entrained rearwards together with the cascade; and a combined movement of the reverser door relative to the cascade, leading to displacement of the front end of the door rearwards along the cascade, and to pivoting of this door, such as to give rise to plunging of its rear end into the secondary flow duct.