Abstract: The control system of the invention includes at least one actuator (6) for a cowling (2), driven by at least one electric motor (7), and a control means (9) for the electric motor (7). The electric motor control means (9) includes a means for determining and/or estimating the outside temperature of the turbojet engine, the electric motor control means being adapted for adjusting the driving torque supplied by the electric motor on the basis of said outer temperature.

Abstract: The invention relates to an acoustic skin (22) for an aircraft nacelle acoustic panel, said skin including a plurality of layers (105, 106) stacked with composite planar bands (102) that are each directed by the direction-defining longitudinal axis (107) thereof, the longitudinal axes (107) of the bands (102) of a single layer (105, 106) being parallel therebetween, said bands (102) of said single layer (105, 106) being spaced from each other so as to have acoustic openings within the acoustic skin. The invention relates to a panel including such a skin, to a method for manufacturing said skin, and to a drape-forming head for implementing the method.

Abstract: The invention relates to an acoustic panel (20) for an ejector nozzle (10) comprising the following main components: an external skin (22) containing acoustic holes (29); an internal skin (23); an acoustic structure (21) comprising alveolar-core cells (27) between the internal skin (23) and the external skin (22). At least one main component selected from the external skin (22), the internal skin (23) and the acoustic structure (21) is formed by a composite material and the acoustic structure (21) is held in contact with either or both of the internal (23) and external (22) skins by compression by elastic means and/or by fixing by mechanical fixing means (24). The invention also relates to an injector nozzle (10) and a nacelle (1) comprising such an acoustic panel (20).

Abstract: The present invention relates to a locking device (10) designed to fixedly attach a first element (9a) to a second element, comprising a locking member (12) intended to equip the first element, an additional locking element intended to equip the second element, and a control handle (13) connected to the locking member via transmission means, characterized in that the transmission means comprise a telescopic connecting rod (15) designed to oscillate freely between a minimum extension position and a maximum extension position, and means for returning the telescopic connecting rod to its position of maximum extension, said return means being placed in a prestressed state when the control handle is in the closure position.

Abstract: This grid thrust reverser cover comprises a seal support and a seal mounted in this support by means of two fastening lugs, this seal being capable of interacting with a diversion edge of this thrust reverser. At least one of the said lugs is turned up and the said support has a section matching that defined by the said lugs.

Abstract: The present disclosure relates to a method for repairing a portion of an acoustic panel for a nacelle of an aircraft turbojet engine. The panel includes an acoustic skin in which a plurality of acoustic holes are drilled, a solid skin, and a cellular acoustic structure. The cellular acoustic structure, being arranged between the acoustic skin and the solid skin, has a plurality of cells, each of which has one or more drainage openings arranged in one or more of the walls forming each cell. The method includes a step of: defining a part of the acoustic panel to be cut; forming a cutting area closed by the acoustic skin; injecting a resin through the acoustic holes; positioning a replacement cellular acoustic structure in the cutting area and on the acoustic skin; forming a solid replacement skin on the replacement cellular acoustic structure.

Abstract: The present invention relates to a jet engine nacelle comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and an aft section equipped with at least one thrust reversal system comprising, on the one hand, means for deflecting at least part of an air flow of the jet engine and, on the other hand, at least one cowl (12) mounted translatably along at least one guide rail (15) in a direction substantially parallel to a longitudinal axis of the nacelle, said movable cowl being able to switch alternately from a closed position, in which it provides the nacelle with aerodynamic continuity and covers the deflection means, to an open position in which it opens a passage in the nacelle and uncovers said deflection means, the nacelle being characterized in that the aft section is equipped with at least one stud (18) mounted such that it can move over a fixed structure of the aft section in the region of the guide rail between a retracted position, in which said stud is withdrawn f

Abstract: The invention relates to a thrust reverser (9) for an aircraft nacelle (1), including: a front frame (11), a cowl (21) which can move between an operating position and an intermediate maintenance position downstream of the front frame (11), means (26) for moving the cowl (21) between closed and open positions, and an inner structure (23) which can move between an operating position and an intermediate maintenance position downstream of the front frame (11). In addition, the cowl (21) comprises two half-cowls (21a, 21b) and the inner structure (23) comprises two structure halves (23a, 23b), whereby said half-cowls (21a, 21b) and said inner structure halves (23a, 23b) can open outward when the cowl (21) and the inner structure (23) are in the intermediate maintenance position.

Abstract: Actuator (V) for opening an aircraft nacelle cowl (7), comprising a dead travel device (19), characterized in that it comprises means (42a, 42b, 43) for blocking the dead travel device (19) when this actuator (V) is extended.

Abstract: A control system of a hydraulic type for a thrust reversal device with which a jet engine nacelle is equipped, and associated with a nozzle variation device, is provided by the present disclosure. The control system includes at least one additional control unit hydraulically connecting actuators together, wherein hydraulic supply lines from the control unit in a nozzle mode and from the control unit in a reverser mode are then able to communicate hydraulically with each other. A plurality of control valves are laid out so that when the unit for driving the actuators in a nozzle mode is active, a corresponding hydraulic signal controls the valves of the control unit in a position such that the hydraulic supply lines of the actuators from the driving unit according to a reverser mode are cut off.

Abstract: A gas shielding device used during a welding step in a controlled atmosphere of a sound attenuation panel includes an inert gas injector to inject inert gas onto the panel and a housing to receive a welding torch. The inert gas injector comprises an inert gas diffuser mounted on the periphery of the housing for receiving the welding torch.

Abstract: The invention relates to a method for making an acoustic panel (12) for an air intake lip (2) of a nacelle (1) that includes the steps of obtaining a perforated de-icing assembly (14) including at least one array of conducting members obtained by a photolithographic method, said de-icing member (14) being secured to a structure with a cellular web (13). The invention also relates to an air intake lip and to a nacelle.

Abstract: An acoustic panel is provided that includes at least one cellular core arranged between at least an internal skin and an external skin, wherein the external skin incorporates at least one fastener able to collaborate in a disconnectable fashion with a complementary fastener associated with a structure to which it is to be attached.

Abstract: A fan duct (5) is defined between an inner skin (2) and an outer skin into which the inner skin of the sliding cover (7) is incorporated in the direct-thrust configuration. The inner skin of the sliding cover (7) comprises an annular part extending radially inwards and capable, in the reverse-thrust configuration, of coming to face a larger-diameter annular part of the inner skin (2) of the fan duct (5). The annular part of the sliding cover (7) comprises at least one flap (8) mounted such that it can pivot between the retracted position and a deployed position in which a front part (8a) of the flap (8), upstream of its middle axis (9) about which it is articulated, projects into the fan duct (5). Translational stop means (11) are provided in order, in the reverse thrust position, to act on a rear part (8b) of the flap (8) in such a way as to cause the flap (8) to pivot into the deployed position to close off the fan duct (5).

Abstract: The invention relates to a turbojet engine nacelle that includes a power supply source (113) for a system for actuating and controlling a thrust reverser device (121), and for a system for actuating and controlling a variable nozzle device (120), characterised in that the power supply can be switched between a first position in which it powers the system for actuating and controlling the thrust reverser device, and a second position in which it powers the system for actuating and controlling the variable nozzle device, wherein the switching is carried out under the action of a control output from a computer (103) capable of receiving a thrust reverser opening control (100).

Abstract: The invention relates to a coupling device (14) intended to connect first and second elements (4, 5) which can move relative to one another, comprising a connecting rod (16) coupled to the first and second movable elements (4, 5) at first and second ends (18, 19) respectively, at least one of the ends of the connecting rod (16) having a head (22) intended to cooperate with locking means (23) belonging to the corresponding movable element (5) so as to removably fasten the connecting rod (16) to the corresponding movable element (5), characterized in that the coupling device (14, 15) comprises at least one telescopic guide member (25) serving to support and guide the connecting rod (16) during the movement of the movable elements (4, 5), having first and second ends (28, 26) intended to be attached to first and second support elements (23, 16) respectively.

Abstract: The invention relates to a locking device (9) designed to be arranged in a junction region of a nacelle, comprising a locking system (10), intended to be mounted on a first half-shell of the nacelle, engaging with a retention member (11) intended to be mounted on a second half-shell, the locking system (10) being actuable between a locked state and an unlocked state with respect to the retention number (11), the locking system (10) and the retention member (11) being movable with respect to one another between a drawn-together position in which they can be locked with respect to one another and a spaced-apart position. The locking system (10) and/or the retention member (11) comprise locking means (25) designed to allow the locking system (10) to be locked with respect to the retention member (11) when they are in the drawn-together position and to prevent them from being locked when they are in the spaced-apart position.

Abstract: A lip of an air inlet of a turbojet pod intended to be fastened to an air inlet downstream structure includes at least one electric heating element for defrosting. The electric heating element being fitted with at least one electrical connector able to be connected to at least one corresponding electricity supply connector of the downstream structure. The lip breaks down into at least two identical structures set end-to-end on a periphery of the air inlet.

Abstract: The invention relates to a propulsion assembly for an aircraft, that comprises: a turbojet engine (1) including a fan casing (3) and an engine casing (5); a pylon for holding said turbojet engine (1); and a device for suspending said turbojet engine under the pylon, that comprises two front suspension connecting rods (9), two rear suspension connecting rods (11), and a thrust acceleration connecting rod (15) extending between the front portion (17) of said engine casing (5) and the pylon in a plane containing the axis (A) of said turbojet engine (1). An additional connecting rod (19) extends between said fan casing (3) and said pylon in a direction substantially parallel to that of the axis (A) of said turbojet engine.

Abstract: A translatable thrust inverter with grids for a turbojet, that defines at least a portion of the downstream section of a nacelle housing the turbojet. The thrust reversal system includes a front frame secured to a fixed portion of the nacelle and bearing. A first side includes cylinders for the translational actuation of at least one mobile cowling. A second side includes grids for inverting the peripheral thrusts, wherein the front frame includes a fixed portion for securing the front frame to the fixed portion of the nacelle and bearing the diversion grids. The system further includes a portion mounted so as to be capable of translational movement along the longitudinal axis of the nacelle and on which one end of the cowling actuation cylinders is attached, wherein the fixed and mobile portions of the front frame can be removably connected to each other by locking means.