Abstract: The present disclosure provides a method of manufacturing a sound absorbing panel in which a reflective wall on one of faces of a set of sound absorbing cells. In particular, a passage on a portion of a thickness (E) of the set of sound absorbing cells is formed on an opposite face of the one of the faces, while the passage forming a main channel for a communication between sound absorbing cells and for a circulation of a de-icing fluid.

Abstract: The present disclosure relates to a nacelle for a dual-flow turbojet engine includes a cold airstream having a non-constant cross-section over the periphery of the nacelle, such that at least one flap is radially offset with respect to the central axis of the turbojet engine, relative to the adjacent flaps. The system for driving the radially offset flaps is suitable for ensuring that the kinematics of the flaps are offset relative to the kinematics of the flaps mounted along the remainder of the periphery of the airstream.

Abstract: A thrust reverser with grids includes a jet engine pylon, a one piece cowl either directly or indirectly slidably mounted on the jet engine pylon between a direct jet position and a reverse jet position, and a system for locking this cowl on a beam. The system has a single tertiary lock, which is positioned on one side of the jet engine pylon being capable of locking a corresponding upper edge of the cowl. In addition, the tertiary lock includes a locker to lock the cowl, a blocker for blocking the locker, and a position detector in order to detect the position of the locker. The system further includes another detector to detect proper closing of the other upper edge of the cowl.

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: A turbojet engine nacelle includes a fixed structure, which has a fan casing of the turbojet engine and a front frame mounted downstream of the fan casing and directly or indirectly supporting cascade vanes. The front frame is able to collaborate with a thrust reverser cowling sliding between a closed position covering the flow-diverting means and an open position exposing this flow-diverting means. At least one reinforcing structure of the engine nacelle transmits load between the fan casing and the front frame. The reinforcing structure extends along the longitudinal axis of the nacelle and supports a third line of defense and/or an inhibiting device between the front frame and the thrust reverser cowling.

Abstract: A bypass turbojet engine nacelle equipped with a thrust reverser device is provided that includes a cowl with translational mobility and a diversion means supported by a front frame upstream of the cowl. A variable-geometry jet pipe nozzle is mounted at a downstream end of the cowl and is translatable in a direction substantially parallel to a longitudinal axis of the nacelle towards at least one position that causes a variation in its cross-section. At least part of the front frame, the diversion means, and the jet pipe nozzle form an assembly having translational mobility in a direction substantially parallel to a longitudinal axis of the nacelle in a downstream direction of the nacelle towards a position that causes a variation in the cross-section of the jet pipe nozzle, the cowl being in the closed position during that movement of said assembly.

Abstract: A nacelle includes a downstream structure having an outer structure, a concentric inner structure surrounding a downstream portion and an upstream section having a relatively small diameter and a downstream section having a relatively large diameter, the inner and outer structures define an annular flow channel. The nacelle includes a guiding system for connecting the inner structure and downstream portion or a portion of a suspension mast, the system combines a translation and rotation movement of at least a portion of the inner structure between a working position, where the inner structure is used as a cowling for the turbojet downstream portion, and a maintenance position where the inner structure exposes the turbojet downstream portion and enable movement of the portion of the inner structure along the profile of the upstream section having a relatively small diameter, and the downstream section having a relatively large diameter.

Abstract: The invention relates to a turbojet nacelle (1) and to an aeroacoustic noise reduction device for said nacelle, the nacelle comprising a nozzle (10) on the downstream end thereof, said nozzle (10) comprising an inner wall inside which a first flow from the turbojet circulates and an outer wall (102) outside which a second flow corresponding to the surrounding outside air circulates. The invention also relates to an aeroacoustic noise reduction device (20) of the turbojet, comprising a plurality of chevrons (201) arranged on the circumference of the nozzle (10). The invention is characterized in that the aeroacoustic noise reduction device also comprises a slide (202) arranged on the circumference of the nozzle in such a way that it can rotate about the axis of the nozzle, each chevron (201) being connected to the slide (202) by means of a guiding element (204) that can move along the slide (202) during the rotation thereof in order to ensure the displacement of the chevron (201).

Abstract: The invention relates to a reverse thrust device including a stationary upstream structure including a front frame (30) and a cowl (40). Said cowl (40) is extended by a nozzle (41) with a variable cross-section and is translatable between a deployed position, causing a variation in the cross-section of the nozzle (41), and a retracted position, wherein the nozzle (41) is in a position wherein it ensures aerodynamic continuity of the cowl (40). Said device is remarkable in that at least part of the front frame (30) is translatable with the cowl (40) during the movement thereof to a position causing a variation in the nozzle cross-section.

Abstract: The present invention relates to a nacelle rear assembly (1) including a pod-shaped internal structure (11), said internal structure comprising at least one downstream portion (15) and one upstream portion (13) that are each movably mounted between an operative position, in which said portions are connected, and at least one maintenance position, in which said portions are separate from each other, the downstream portion being movably mounted by means of sliding while the upstream portion is movable by opening at least one door. The downstream portion and upstream portion are provided with a connection means that is capable of engaging therebetween. Said assembly is characterized in that at least one of the downstream and upstream portions is provided with a hinging means (131, 151) having a range of movement in at least one direction so as to enable stress-free control and operation of the portion in question.

Abstract: The invention relates to an assembly for a turbojet engine which includes a pylon (1) and a nacelle supported by said pylon (1). Said nacelle (3) includes a grid thrust reverser (21) including an integral cowl mounted so as to slide on rails (15), which are arranged on both sides of said pylon (1), between a direct jet position and a thrust reversal position. Said assembly is characterised in that it includes means (23, 31) for blocking the sliding movement of the cowl on the rails (15), said means being inserted between the pylon (1) and the cowl.

Abstract: The present invention relates to a thrust inverter for a turbojet engine nacelle (1) including at least one outer cowl (11) that is movable between a closed position and a thrust inversion position, said movable cowl also being able to be opened into a supporting position towards which said movable cowl is hinged and guided through the use of a guiding means that is suitable to said movable cowl and located substantially on a pylon, to which the nacelle is intended to be attached and at least one front frame (15) capable of being mounted downstream from an air blower housing for said turbojet engine and directly or indirectly holds at least one flow diversion means (12). Said thrust inverter is characterized in that the front frame is detachably connected to the housing in a translatable manner along at least one related guiding member (17) once said front frame is detached from the housing.

Abstract: The invention relates to an assembly for holding the interface of a stationary outer structure (15) of a nacelle (3) and housing (27) of a jet engine (5), said assembly including: a first raised element belonging to the upstream end of the stationary outer structure (15); a second raised element belonging to the downstream end of the housing (27), said first and second raised elements being formed so as to be placed in contact with each other; two half-rings (109) formed by a wall defining a recess that is formed so as to receive the first and second raised elements when the housing (27) and the stationary outer structure (15) are mounted edge to edge; and an abutment means formed so as to keep the first and second raised elements in the recess.

Abstract: The invention relates to a jet engine nacelle reverse thrust device (10) including a means for diverting at least one portion of a jet engine air flow and moreover includes at least one cowl (20) that is translatable in a direction substantially parallel to a longitudinal axis of the nacelle, the device having at least one flap (30) that is pivotably mounted, by one end, onto the translatable cowl, said translatable cowl (20) being capable of passing alternately from a closed position, wherein said cowl, with the flap (30) in a retracted position, ensures the aerodynamic continuity of the nacelle and covers the diverting means, to an open position, wherein said cowl opens a passage in the nacelle and uncovers the diverting means, the flap (30) being in a pivoted position wherein it is capable of sealing off a portion of an annular channel of the nacelle.

Abstract: The invention relates to a de-icing device (1) in particular for an aircraft nacelle comprising at least two electric bands (5) each made from at least one main conductor (7) oriented substantially along the length of said band (5), characterised in 11 that said bands (5) comprising rectilinear elements (13) and bent elements (17), and in that said bands (5) comprising spirals (15) formed by the association of several bent elements (17), and in that the contiguous bands (5) are embedded together at least in pairs.

Abstract: The invention relates to a suspension assembly for an aircraft turbojet engine (3), including a pylon (1) up and connected to the pylon (1), and connecting rods (13a, 13b) for taking up the thrust of the turbojet engine (3) remarkable in that the assembly includes means (19a, 19b; 25) separate from said pylon for thermally insulating the connecting rods (13a, 13b) from the turbojet engine (3).

Abstract: The invention relates to a thrust reverser for a turbofan engine nacelle including a stationary portion (15) downstream from which is mounted at least one cowl (9) movable between a direct-jet position, in which the cowl (9) is aligned with the stationary portion (15), and a thrust-reversal position, in which the mobile cowl (9) is spaced apart from the stationary portion (15) so as to define an opening for the passage of a secondary flow (F), a means for deflecting (16) the secondary flow (F) through the passage opening, an actuator means (45) and a means (24) for guiding the mobile cowl (9) relative to the stationary portion (15), at least a first and a second adjacent cascade vane (13), positioned at an angle (B) relative to the movement axis (A) of the mobile cowl (9), arranged opposite the passage opening such that the deflected secondary flow (F) at least partially passes through the first and second vanes (13) in order to increase the deflection of said secondary flow (F) in the upstream direction, sai

Abstract: This strut (9), designed to support an aircraft turbojet engine, has, on the one hand, a connecting part (11) for connection between the casing (1) of the fan (3) or the casing of the gas generator (5) of the said turbojet engine and a wing of the said aircraft and, on the other hand, a Y-shaped box-section part (19), secured to the said connecting part (11) and designed to form the upper part of the inner fixed structure of the said nacelle.

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: The invention relates to a turbojet nacelle (1) and to an aeroacoustic noise reduction device for said nacelle, the nacelle comprising a nozzle (10) on the downstream end thereof, said nozzle (10) comprising an inner wall inside which a first flow from the turbojet circulates and an outer wall (102) outside which a second flow corresponding to the surrounding outside air circulates. The invention also relates to an aeroacoustic noise reduction device (20) of the turbojet, comprising a plurality of chevrons (201) arranged on the circumference of the nozzle (10). The invention is characterised in that the aeroacoustic noise reduction device also comprises a slide (202) arranged on the circumference of the nozzle in such a way that it can rotate about the axis of the nozzle, each chevron (201) being connected to the slide (202) by means of a guiding element (204) that can move along the slide (202) during the rotation thereof in order to ensure the displacement of the chevron (201).