Abstract: A method of braiding reinforcing fibers on a mandrel (8) with a machine having a ring (9) carrying at least two series of reels of fibers, by moving the mandrel at a predetermined forward speed while moving the two series of reels along the ring (9) so that they cross while rotating in opposite directions and at a predetermined speed of rotation about an axis (AX) of the ring. The braid is formed on the mandrel (8) in the vicinity of a region of convergence (R) of the fibers that together define a conical shape (C). The method comprises: a step of reconfiguring the machine in which the angle (a2) at the apex of the cone (C) defined by the fibers takes on a new value (a2); and a step of restarting braiding in which the movement of the reels along the ring (9) and the forward movement of the mandrel (8) are re-established with a new speed of rotation and a new speed of advance.

Abstract: The invention relates to a method for the self-calibration of electric jacks (6a, 6b) capable of actuating a mobile member (2) of a turbojet nacelle (1) and connected to at least one position measuring member, characterized in that it comprises the steps of: moving the jack(s) into a retracted position corresponding to a first position of the mobile member, storing one or more position values fed back by the position measuring member for the jack(s) in said retracted position; moving the jack(s) into an extended position corresponding to a second position of the mobile member; storing one or mom position values fed back by the position measuring member for the jack(s) in said extended position.

Abstract: The invention relates to a method for controlling a plurality of actuators (9a, 9b, 9c) for a movable thrust reverser cowl (1), characterized remarkable in that the position deviation between adjacent actuators is measured in real time, and in that the speed profile of the actuator or actuators in question is adjusted by a position deviation exceeding a predetermined threshold.

Abstract: The invention relates to a nacelle for a turbojet, of the type comprising a downstream structure having an outer structure (6) that defines, together with an inner concentric structure (9) for surrounding the downstream portion of the turbojet, an annular flow channel (8), characterised in that a portion at least of said inner structure (9) is mounted so as to be capable of a translation movement along the longitudinal axis of the nacelle so that it can move between a working position, in which the inner structure acts as a casing for the downstream portion of the turbojet, and a maintenance position in which the inner structure exposes said downstream portion of the turbojet.

Abstract: The invention relates to a linear telescopic actuator for moving a first (10b) and a second (10a) element relative to a stationary element (102). Said actuator comprises a base (101) that is to be connected to the stationary element (102) and is used as a cavity for a first rotationally locked rod (106) which can be translated by a drive shaft (104) that is to be connected to rotational driving means (107). One end (108) of said first rod is to be connected to the first element that is to be moved. The actuator is characterized in that the first rod (106) supports a second rod (117) which is aligned therewith and one end (118) of which is to be connected to the second element that is to be moved. Said second rod (117) can be rotationally locked and can be translated by a second drive shaft (112, 115) which extends through the base and is connected to rotational driving means (113, 111).

Abstract: The invention relates to a rear section (11) of an aircraft nacelle, that comprises two halves (13a, 13b) defining: a central portion (C) for receiving a turbojet engine (7), a cool-air annular passage (31) provided around said central portion (C), and at least one six-hour cavity (15) provided under said central portion (C). The rear section is characterized in that it comprises at least one duct (29a, 29b) for the fluidic communication between said annular passage (31) and said six-hour cavity (15) for maintaining the temperature inside the six-hour cavity (15) within a relatively low range.

Abstract: The disclosure relates to a nacelle for a turbojet engine, including an upstream section forming an air intake lip and defining a space for the circulation of a main air flow. The nacelle includes a device for modulating the cross-section of the space and has means for injecting an auxiliary flow of a gas by means of an induced ejector effect; suction means for drawing in the injected auxiliary flow; and an internal auxiliary flow return area in one or more walls, the area being configured to allow the circulation of the injected auxiliary flow and the drawn-in auxiliary flow and to bring part of the injected auxiliary flow into contact with the main air flow. The internal return area includes an outer front part forming an area in which the thickness of the internal return area is reduced.

Abstract: An aerodynamic element for an aircraft nacelle is provided that includes a fixed shroud and an intake lip axially movable relative to the shroud. The aerodynamic element is flexible and has a substantially cylindrical general shape and defines an upstream portion attached to the inner wall of the intake lip of the nacelle, and a downstream portion bearing radially against an inner face of the shroud. The downstream portion of the element includes a ring shaped bead protruding towards an outside of the aerodynamic element and an end blade which, at rest, is tilted towards the outside of the aerodynamic element in a direction of its free end.

Abstract: A nacelle for a turbojet engine includes an air inlet forward section, a median section surrounding a fan of the turbojet engine, an aft section equipped with a thrust reverser system, a power control unit able to convert a high voltage electric supply into an electric supply towards an electromechanical actuator, and a drive unit for the power control unit which is distinct and separate from the latter and has a control input and a drive output to be connected to the power control unit. The thrust reverser system includes a mobile cowl which, under action of an electromechanical actuator, is able to move from a closed position to an open position in which the mobile cowl opens a passage in the nacelle.

Abstract: A thrust reverser for a turbojet engine includes a telescopic linear actuator for a moving cowl and a nozzle-forming end part. The telescopic linear actuator has a base attached to a fixed frame, acting as a housing for a first rod prevented from rotating but able to be translationally driven by a first drive shaft connected to a rotational-driver. The first rod is attached by one end to the moving cowl and supports a second rod, which is attached by one end to the nozzle-forming end part that is to be moved. The second rod is prevented from rotating and translationally driven by a second drive shaft passing through the base and connected to a rotational-driver. In particular, the rotational-driver of the rods includes a motor to drive an input shaft of a differential having two output shafts.

Abstract: A seal assembly for a turbojet nacelle includes a first end fastened to a first structure, and a second end contacting against a bearing zone of a second structure. The seal assembly further includes a plurality of adjacent blades arranged along the first end and extending longitudinally and perpendicularly thereto. In particular, a portion of the blades has an accordion-shaped structure.

Abstract: A de-icing device for an aircraft nacelle includes two electric bands, and each of them is made from one main conductor oriented along a length of the band. In particular, the two electric bands have rectilinear elements and bent elements and are located on a same plane. Moreover, the two electric bands include spirals formed by association of several bent elements. Contiguous bands are embedded together in pairs, and the embedded bands are powered by different power supplies.

Abstract: The invention relates to a guiding device (100) for part of a jet engine nacelle that can move in translation, comprising: (i) a rail (101) fixedly mounted on part of the nacelle, and (ii) a slide (102) which is connected to the mobile part and which can slide along the rail. The invention is characterized in that the guiding device is provided with a built-in retractable system for preventing the translational movement of the slide, for which purpose the device includes: (i) at least one blocking means (104) mounted such that it can move on the rail and occupy alternatively an engaged position in which it forms a translational abutment for the slide and a released position in which it is moved away from the slide and enables the relative translational movement of the slide beyond the locking system, and (ii) at least one means (130) for controlling the blocking means.

Abstract: The present disclosure relates to a thrust reverser including at least one translatably movable cowl capable of alternately shifting between a closed position in which same ensures the aerodynamic continuity of the nacelle and which covers the deflecting means, and an open position in which same opens a passage in the nacelle and uncovers the deflecting means, said thrust reverser likewise including at least one variable nozzle section arranged in the extension of the movable thrust-reversing cowl and provided with at least one locking means capable of engaging with a complementary locking means of the movable reversing cowl so as to optionally mechanically link the movable nozzle section of the movable reversing cowl.

Abstract: The invention relates to a nacelle that comprises a fixed structure (20), a nozzle with a variable section, and a cowling (30) mounted on said fixed structure (20) so as to be capable of sliding particularly along a travel so as to modify the section of said nozzle, characterized in that the nacelle further comprises an aerodynamic continuity assembly (40) provided between the fixed structure (20) and the mobile cowling (30), said assembly (40) including an elastic means that can be compressed between the fixed structure and said mobile cowling when the cowling is in the upstream portion of the travel thereof and that can expand when the cowling is in the downstream portion of the travel thereof so as to ensure the aerodynamic continuity of the lines between said fixed structure (20) and said mobile cowling (30).

Abstract: A nacelle for receiving an aircraft engine, the nacelle having a tubular stationary cover and at least one movable portion connected to the stationary cover via movement means for moving the movable portion between a position close to the stationary cover and a position spaced apart therefrom. The movement means have asynchronous motors, each having a stator with windings connected in parallel to a power supply circuit and a rotor having windings, each connected to a resistive load in parallel with a winding of the rotor of each of the other motors.

Abstract: A thrust reverser for the nacelle of a turboreactor includes at least one fixed front frame that can be mounted downstream of a fan casing of the turboreactor and directly or indirectly supports at least one flow deviation vanes, in which at least part of the flow deviation vanes can be detached from the front frame and moved in translation independently therefrom when a maintenance operation is being carried out on the reverser.

Abstract: An aircraft turbojet engine air intake structure includes an air intake lip provided with a first acoustic attenuation panel which contains a structuring skin and, as an acoustic absorption material, a porous material fastened on the skin. The air intake structure also includes a pneumatic de-icing compartment defined by the lip and by an inner partition. The first acoustic attenuation panel is of the type including an open-cell porous material which is capable of resisting a temperature of up to 200° C. and having high heat conductivity.

Abstract: The present invention relates to a nacelle (1) for a jet engine (4) comprising a forward air inlet section (5), a mid-section (6) intended to surround a jet engine fan, and an aft section (9), at least one portion forming the aft section being connected to the mid-section via an at least partially peripheral radial knife-edge (31) capable of engaging by complementarity of shape with a corresponding groove (32) belonging to a portion (6a) of the mid-section, characterized in that the knife-edge comprises at least one reinforcing segment (35, 36) situated in a region for accommodating high loads, said reinforcing segment being made from a material which is stronger than the remainder of the knife-edge and tailored to the loads which are to be borne by said segment in this region.

Abstract: The invention relates to a nacelle for a turbojet engine that includes an air intake structure capable of directing an air flow towards a fan of the turbojet engine, and a middle structure for surrounding said fan and to which is attached the air intake structure in order to provide aerodynamic continuity, wherein the air intake structure includes at least one inner panel attached to the middle structure and defining, with the latter, a nacelle fixed structure and at least one outer longitudinal panel removably attached to the fixed structure and including an air intake lip in order to define a removable air intake structure, wherein the removable air intake structure is provided with a locking device including at least one electric lock capable of interaction with a complementary retention structure.