Abstract: A front engine attachment, intended to fix an engine to a structure of an aircraft, includes a first attachment including a base intended to be fixed to the structure, a first fixture articulated on the base, two first connecting rods, each being articulated by a first end to the engine and by a second end to the fixture, and a first cylindrical nose mounted on the base. The front engine attachment includes a second attachment including a cradle including an orifice into which the cylindrical nose is fitted, and a second cylindrical nose being threaded into a piercing of the engine, and two second connecting rods, each being intended to be articulated by a first end to the engine, and by a second end to the cradle.

Abstract: An aircraft nacelle comprising a first and a second cowl mounted pivotably about an axis substantially parallel to a longitudinal axis of the nacelle and lockable to one another by at least one locking mechanism. The nacelle further comprises a device for providing a visual warning of a locking defect of the cowls. The device comprises a movable bolt associated with the locking mechanism and a movable edge plate mounted on the nacelle in line with said bolt with which it is associated, the movable edge plate being movable under the action of an operator between a protruding position, in which the edge plate is protruding from the nacelle and a locking mechanism is in an unlocked position, and a retracted position, in which the edge plate is immobilized within the nacelle by the bolt and the action of the locking of a locking mechanism.

Abstract: A propulsion assembly having a heat exchanger and a system for supplying cold air including an air inlet in a stream of air, an air duct connecting the air inlet fluidly to the exchanger, and an air flow valve with a variable flow rate inside the duct, the valve including a hub having blades projecting radially from the hub forming a helix, each blade having a root mounted rotatably on the hub, the valve comprising an electric motor to drive the hub by a motor shaft, and structure for varying pitch angle of the blades, the extremity of each blade being flush with a wall of the duct, the valve controllable to a closed configuration where pitch angle of the blades is 0° and the valve prevents passage of air, an open configuration where pitch angle is 90°, and/or a charge configuration where pitch angle is between 0° and 90°.

Abstract: A damage detection and repair system is provided for performing a damage detection and repair preparation process, and includes an image-capturing device having at least one camera lens, a first positional sensor, and an orientation sensor. At least three second positional sensors are provided for the object to detect a corresponding three-dimensional (3D) position of the object relative to the image-capturing device. A location determination module determines a positional information of the damage of the object based on signals received from the first positional sensor, the orientation sensor, and the second positional sensors. A 3D generation module generates a 3D digital mockup model for illustrating the damage of the object and associated parts needed for repairing the damage.

Abstract: An engine assembly for an aircraft, comprising a mast. The engine assembly comprises an engine with a horizontal engine axis, an engine shaft having a first end rigidly connected to the engine and a second end, and a reducer having an input shaft meshing with the second end, and an output shaft to which a propeller is fixed. The engine assembly is configured such that the engine is fixed to the mast by a rigid connection, the reducer is fixed to the mast by means of flexible fasteners, the rotation between the engine shaft and the input shaft being driven via a slide link, the engine shaft has a first part and a second part and, therebetween, a flexible part assuring a tolerance to an angular misalignment between the axis of the second part and the axis of the first part.

Abstract: A damage detection and repair system is provided for performing a damage detection and repair preparation process, and includes an image-capturing device having at least one camera lens, a first positional sensor, and an orientation sensor. At least three second positional sensors are provided for the object to detect a corresponding three-dimensional (3D) position of the object relative to the image-capturing device. A location determination module determines a positional information of the damage of the object based on signals received from the first positional sensor, the orientation sensor, and the second positional sensors. A 3D generation module generates a 3D digital mockup model for illustrating the damage of the object and associated parts needed for repairing the damage.

Abstract: A front engine attachment, intended to fix an engine to a structure of an aircraft, includes a first attachment including a base intended to be fixed to the structure, a first fixture articulated on the base, two first connecting rods, each being articulated by a first end to the engine and by a second end to the fixture, and a first cylindrical nose mounted on the base. The front engine attachment includes a second attachment including a cradle including an orifice into which the cylindrical nose is fitted, and a second cylindrical nose being threaded into a piercing of the engine, and two second connecting rods, each being intended to be articulated by a first end to the engine, and by a second end to the cradle.

Abstract: A propulsion assembly having a heat exchanger and a system for supplying cold air including an air inlet in a stream of air, an air duct connecting the air inlet fluidly to the exchanger, and an air flow valve with a variable flow rate inside the duct, the valve including a hub having blades projecting radially from the hub forming a helix, each blade having a root mounted rotatably on the hub, the valve comprising an electric motor to drive the hub by a motor shaft, and structure for varying pitch angle of the blades, the extremity of each blade being flush with a wall of the duct, the valve controllable to a closed configuration where pitch angle of the blades is 0° and the valve prevents passage of air, an open configuration where pitch angle is 90°, and/or a charge configuration where pitch angle is between 0° and 90°.

Abstract: An aircraft nacelle comprising a first and a second cowl mounted pivotably about an axis substantially parallel to a longitudinal axis of the nacelle and lockable to one another by at least one locking mechanism. The nacelle further comprises a device for providing a visual warning of a locking defect of the cowls. The device comprises a movable bolt associated with the locking mechanism and a movable edge plate mounted on the nacelle in line with said bolt with which it is associated, the movable edge plate being movable under the action of an operator between a protruding position, in which the edge plate is protruding from the nacelle and a locking mechanism is in an unlocked position, and a retracted position, in which the edge plate is immobilized within the nacelle by the bolt and the action of the locking of a locking mechanism.

Abstract: A propulsion unit comprising a turbofan engine faired by a nacelle, and held in suspension by at least one pylon, the turbofan engine including a fan; a duct, bounded by an internal surface of the duct and an inner surface of the nacelle, that channels air accelerated by the fan; and a thrust reverser including a first part and a second part, wherein the turbofan engine has a first circumferential sector and a second circumferential sector distinct from the first circumferential sector, wherein the first circumferential sector and the second circumferential sector span the entire turbofan engine, the first part is entirely within the first circumferential sector and includes doors that channel the air in the duct towards an exterior of the nacelle via openings, and the second part is entirely within the second circumferential sector and includes mobile elements that channel the air in the duct toward the doors.

Abstract: An aircraft engine assembly including a mounting pylon including a rigid structure fitted with a central box, together with a forward extension and a rear extension each including an attached upper organ supported on an upper surface of the central box, and an attached lower organ supported on a lower surface of the front end. The forward and rear extensions support at least a part of the first fasteners interposed between the rigid structure and a turbine engine.

Abstract: An engine assembly for an aircraft, including a rigid structure including a box rib extension protruding from a box of the structure, in a line of separation, towards a fuselage of the aircraft. The extension supports a first attachment in a position separating it from a second attachment in the line of separation. The first and second attachments enable the moment being exerted in a lengthways direction of the turbine engine to be transmitted jointly.

Abstract: An aft part of an aircraft, including at least one engine assembly including a turbine engine and a turbine engine mounting pylon. A rigid structure of the mounting pylon includes a longitudinal central box and a connection box carried by the box and projecting from the box. The aircraft structure includes a fuselage lateral extension projecting from it, and the connection box is pressed into contact with the fuselage extension, below it, an attachment mechanism being arranged between these two entities.

Abstract: An engine attachment pylon for an aircraft, including a rigid structure including a box formed by one or plural hollow segments. The section of at least one hollow segment is circular or elliptical in shape.

Abstract: This invention relates to a force transmission system (50) between a turboprop and an attachment pylon, comprising: a first and a second force transmission device (52a, 52b) each comprising a first hollow cylinder (54) with an axis (56) that will be made parallel to a first force transmission direction, said first cylinder defining a first space (58) full of a fluid (60) and closed off in a sealed manner at its two opposite ends, by a first damping layer (62) that will bear in contact with a bearing element (66) of the turboprop, and by a second damping layer (64) that will bear in contact with a bearing element (68) of the attachment device, said first and second layers possibly being compressed by the pressure of said fluid; and first means (70) of fluid communication between the two spaces (58, 58).

Abstract: An engine attachment pylon for an aircraft including a rigid structure including a box including an upper spar and a lower spar, connected to each other through two lateral panels. At least one of the upper and lower ends of the web of at least one of the two lateral panels includes at least one assembly cleat projecting sideways from the web towards the outside of the box, and assembled to the spar on which it bears through an attachment mechanism located outside the inner space in the box.

Abstract: A jet propulsion unit of an aircraft, which comprises a turbofan engine (3) faired by a nacelle (1), further comprising a thrust reverser device in two parts: one part and including a means for flowing back the air (15) towards the outside of the propulsive unit, in a first angular sector of the nacelle; one part including internal backflow means which can be removed and controlled, suitable for channeling the secondary air flow, circulating in a secondary duct between the propulsive unit and the nacelle, in a second angular sector of the nacelle such as to offset the latter angularly in the secondary duct towards some external thrust reverser means.

Abstract: Aircraft nacelle which includes a cowl with a longitudinal axis, an engine housed in the cowl, an annular channel surrounding the engine and designed to receive a secondary flow, wherein the cowl includes a fixed part and a moving part which slides along the longitudinal axis to define a radial opening between the moving and fixed parts, a thrust reverser system which includes internal flaps mounted so that they rotate and which are designed to block the annular channel, at least partially, in the deployed position, where the moving part of the cowl includes a radial housing to receive the internal flaps in the at-rest position and where a system of applying an elastic force on each flap towards deployment is provided. Thus control over the position of the internal flaps is obtained directly by sliding the moving part.

Abstract: An aircraft engine assembly including a mounting pylon including a rigid structure fitted with a central box, together with a forward extension and a rear extension each including an attached upper organ supported on an upper surface of the central box, and an attached lower organ supported on a lower surface of the front end. The forward and rear extensions support at least a part of the first fasteners interposed between the rigid structure and a turbine engine.

Abstract: The invention relates to an aircraft turbine engine and to the use of such a turbine engine. According to the invention, the turbine engine (la) comprises a means for shifting the axis (la-la) of the blower (9a) transverse to the axis (La-La) of the hot flow generator (4a).