Abstract: A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.

Abstract: A turbofan having a nacelle comprising a slider mobile in translation between an advanced and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one mobile in rotation on the slider between a stowed and a deployed position, where the blades are split into groups, where each group comprises a first blade, and a maneuvering system moving each blade and comprising a cam integral with the first blade of one of the groups and having a tooth, a groove receiving the tooth, a first transmission system transmitting the movement of the first blade bearing the cam to a first blade of each other group, and, for each group, a second transmission system transmitting the movement of the blade that bears the cam or is moved by the first transmission system to each of the other blades of the group.

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 method for connecting two components is proposed where a pressure acting on an adhesive between two join partners is supported by an auxiliary body which rests on a cutout of one of the components. Both components to be connected together and the auxiliary body are covered by a vacuum film and once the air has been sucked out, the compressive force is generated below the vacuum film.

Abstract: A turbofan including a motor, nacelle and a secondary duct therebetween. The nacelle includes a fan casing with front and rear parts, a fixed assembly including a fixed structure and the front part, a mobile assembly with an openwork frame, a mobile cowl and the rear part and mobile between advanced and retracted positions in which a window is open between the secondary duct and the exterior of the nacelle, inner doors articulated between stowed and deployed positions, a first actuator for moving the frame and a second actuator for moving each inner door. The rear part is divided into outer flaps mobile between lowered and raised positions and is moved by an electric motor. A jet engine accordingly serves to increase retraction distance by freeing up part of the fan cowl and improve orientation of flow of air passing through the window by orienting the outer flaps.

Abstract: A turbofan comprising a motor and a nacelle, surrounding the motor, where a duct for a bypass flow is delimited between the nacelle and the motor and in which a flow of air flows. The nacelle comprises reverser flaps where each one is articulated between a stowed position in which it is not in the bypass duct and a deployed position in which it is across the bypass duct. The turbofan has at least one reverser flap with at least one leakage window configured to allow airflow in the deployed position. The at least one reverser flap has at least one fin extending across the leakage window.

Abstract: A turbojet engine comprising an engine, a nacelle comprising a fan case, an intermediate case having a part forming a hub and an outer shroud radially spaced away from the hub by a secondary, or bypass, flow path and fixed to the hub via arms, in which the outer shroud is situated to the rear and in the continuity of the fan case, a fixed structure fixed to the outer shroud, a mobile assembly mounted with the ability to effect translational movement on the fixed structure, and a ramp fixed to the outer shroud and configured to direct the secondary or bypass flow to exit the outer shroud. Such a turbojet engine makes it possible to simplify assembly and among other things, makes it possible to fix the ramp directly to the outer shroud.

Abstract: A turbofan with a fan casing and a nacelle which comprises a fixed structure, a movable assembly with a movable cowl and a slide, which is translationally movable between an advanced position and a retreated position in which the movable cowl is moved away from the fan casing in order to define a window open between a duct and the outside of the nacelle, a plurality of blades, each being mounted rotatably on the slide, where each blade is movable between a retracted position in which the blade is outside of the duct and a deployed position in which the blade is across the duct, a set of actuators for moving the slide and an operating system configured to move each blade from the retracted position to the deployed position, and vice versa.

Abstract: An aircraft engine attachment configured to be inserted between an engine and an EMS, the attachment including a plate assembly connected to a first fixing device including an end fitting with two arms and a pin passing through the plate assembly and the two arms, in each of which an orifice is formed including a first ring and a second ring respectively holding the pin. The first ring includes a bottom acting as a stop for a first end of the pin, and the first attachment device includes a mechanism to stop the pin in translation cooperating with a second end of the pin.

Abstract: A connection assembly of an engine pylon underneath an aircraft wing, the wing being provided with a fitting, the engine pylon being provided with a fork joint nested in the fitting and fixed to the said fitting by means of a traversing pin system, including: an external primary pin, a secondary pin mounted inside the primary pin, a primary shoulder mounted directly around the primary pin, at a blind end of the pin system, to block the said pin in translation, a secondary shoulder mounted around one end of the secondary pin, at a blind end of the pin system, to block the system in rotation, and an interlocking assembly mounted around the primary pin and the secondary pin, at a free end of the pin system, to block the pin system in translation.

Abstract: An aircraft engine attachment device including a rigid structure and a mechanism attaching the engine on the rigid structure, the attachment mechanism including a rear engine attachment and a device for taking-up thrust forces generated by the engine. The rear engine attachment is attached to the rigid structure by two lateral fittings attached to the rigid structure. The force take-up device includes two connecting rods mechanically connected to a spreader beam by a mechanical connection, a connection fitting attached to the rear engine attachment and mechanically connected to the rigid structure by a thrust pin, the lateral fittings including a stop mechanism to limit pivoting of the spreader beam if a connecting rod breaks and ensuring transmission of thrust forces to the rigid structure.

Abstract: An aircraft assembly including a wing element and an attachment pylon of a turboengine, including a rigid structure forming a caisson defined externally by a first longeron, a second longeron, and two lateral panels. The assembly also includes an attachment mechanism of the structure on the wing element, fitted with two front attachments, each including two first fittings solid with the associated lateral panel. For each front attachment, the two first fittings are arranged respectively on either side of their associated lateral panel.

Abstract: The invention relates to a connection assembly of an engine pylori underneath an aircraft wing, the wing being provided with a fitting (6), the engine pylori being provided with a fork joint (5) nested in the fitting and fixed to the said fitting by means of a traversing pin system (10), provided with: an external primary pin (11), a secondary pin (12) mounted inside the primary pin, a primary shoulder (13) mounted directly around the primary pin, at a blind end of the pin system, to block the said pin in translation, a secondary shoulder (14) mounted around one end of the secondary pin, at a blind end of the pin system, to block the system in rotation, an interlocking assembly (15, 16) mounted around the primary pin and the secondary pin, at a free end of the pin system, to block the pin system in translation.

Abstract: An aircraft engine attachment device including a rigid structure and a mechanism attaching the engine on the rigid structure, the attachment mechanism including a rear engine attachment and a device for taking-up thrust forces generated by the engine. The rear engine attachment is attached to the rigid structure by two lateral fittings attached to the rigid structure. The force take-up device includes two connecting rods mechanically connected to a spreader beam by a mechanical connection, a connection fitting attached to the rear engine attachment and mechanically connected to the rigid structure by a thrust pin, the lateral fittings including a stop mechanism to limit pivoting of the spreader beam if a connecting rod breaks and ensuring transmission of thrust forces to the rigid structure.

Abstract: An aircraft assembly including a wing element and an attachment pylori of a turboengine, including a rigid structure forming a caisson defined externally by a first longeron, a second longeron, and two lateral panels. The assembly also includes an attachment mechanism of the structure on the wing element, fitted with two front attachments, each including two first fittings solid with the associated lateral panel. For each front attachment, the two first fittings are arranged respectively on either side of their associated lateral panel.

Abstract: The manufacturing of electronic components on individual substrates made of an insulating material includes molding, in a silicon wafer, an insulating material with a thickness corresponding to the final thickness desired for the substrates, manufacturing the electronic components, and removing the silicon from the rear surface of the wafer after manufacturing of the components.

Abstract: A method for manufacturing an inductance in a monolithic circuit including a substrate of planar upper surface, including the steps of forming in the substrate a cavity substantially following the contour of the inductance to be formed, the cross-section of the cavity being deep with respect to its width; and filling the cavity with a conductive material.

Abstract: An aircraft engine attachment configured to be inserted between an engine and an EMS, the attachment including a clevis connected to a first fixing device including an end fitting with two arms and a pin passing through the clevis and the two arms, in each of which an orifice is formed including a first ring and a second ring respectively holding the pin. The first ring includes a bottom acting as a stop for a first end of the pin, and the first attachment device includes a mechanism to stop the pin in translation cooperating with a second end of the pin.

Abstract: The manufacturing of electronic components on individual substrates made of an insulating material includes molding, in a silicon wafer, an insulating material with a thickness corresponding to the final thickness desired for the substrates, manufacturing the electronic components, and removing the silicon from the rear surface of the wafer after manufacturing of the components.

Abstract: A method for handling a thin silicon wafer including the steps of successively forming on a surface of the wafer a first protection layer, a first etch stop layer, and an external layer; forming on a surface of a support wafer a gluing layer of the same material as the external layer of the wafer, the surface of the support wafer including a plurality of pads, the respective upper portions of which are substantially planar and coplanar; fastening, by direct gluing, the external layer of the wafer and the gluing layer of the support wafer; processing the wafer to form circuits therein; depositing a second protection layer on the wafer surface which is not glued to the support wafer; and removing by an etch process the material forming the external layer of the wafer and the gluing layer of the support wafer.