Abstract: An assembly includes a nacelle panel of an aircraft engine, the nacelle panel including an outer skin, an inner skin and a central layer interposed between the outer and inner skins. The central layer has a housing, the outer skin has an opening which opens into the housing, and a linking member extends in the opening and in the housing, the linking member to be connected to an actuator.

Abstract: Disclosed is an air intake of an aircraft turbine engine nacelle having a lip, a downstream portion and an internal partition separating the lip and the downstream portion, the lip delimiting an annular recess, the downstream portion having a downstream inner wall and a downstream outer wall, the air intake having an injection channel for injecting a hot air stream into the annular recess, a passage opening formed in the internal partition, an outlet opening formed in the downstream outer wall and a discharge channel for discharging the hot air stream mounted in the downstream portion and having a first end connected to the internal partition, a second end connected to the downstream outer wall and a main body having at least one flexible portion.

Abstract: A thrust reverser for a propulsion unit, incudes movable grids, two half-assemblies forming part of a secondary stream and, at the six o'clock position, a connecting beam intended to be mounted in cantilever with a fan housing. The half-assemblies are hinged at the twelve o'clock position so as to enable their “butterfly” movement between a flight configuration and a maintenance configuration. The connecting beam includes a connecting member configured to cooperate, in the form of a tenon and groove connection, with the half-assemblies when these are in flight configuration. The reverser also includes, downstreamof the connecting member, locks capable of locking the half-assemblies in flight configuration.

Abstract: An aircraft having an airframe with several airframe elements and at least one fluidic propulsion device with a peripheral nozzle defining an internal cavity in which an external airflow circulates, the peripheral nozzle having openings configured to inject a plurality of high-speed airflows into the internal cavity so as to accelerate the external airflow in an upstream to downstream manner. A portion of the peripheral nozzle can be integrated into an airframe element so as to enable acceleration of an external airflow circulating from upstream to downstream on said airframe element so as to improve its re-adhesion to said airframe element.

Abstract: An air intake scoop intended to be fastened on a panel of an aircraft includes an air inlet mouth having a wall, a peripheral collar intended to be fastened to the panel, and a bearing element intended to support the air circulation duct. The air inlet mouth is made of a thermoplastic material and the bearing element is fastened on the peripheral collar so as to achieve a pressure barrier in case of breakage of the wall of the air inlet mouth.

Abstract: A thrust reverser of a nacelle of a turbojet engine of an aircraft extending about a longitudinal axis and including a fixed structure and at least one door which is rotatable between a closed position and an open position and including a downstream frame spaced axially from a downstream end edge of the door by an axial clearance parallel to the longitudinal axis. The thrust reverser includes a system for diverting fluids to the exterior including at least one projection fixed onto the door or the other fixed structure and extending into the axial clearance and towards one of the fixed structure or the door, while leaving an axial gap between a free end of said projection and one of the fixed structure or the door.

Abstract: An aircraft turbojet engine nacelle includes a rear section without a lower bifurcation, the rear section including a thrust reverser system, and the thrust reverser system including a movable cowl. The nacelle includes a guide system including a movable portion and a fixed portion, the movable portion being secured in translation to the movable cowl and cooperating with the fixed portion and the fixed portion being fixed relative to the nacelle. The guide system is disposed proximate to a position called the “6 O'clock” position. In one form, the length of the fixed portion of the guide system is larger than or equal to 50% of the length of the movable portion.

Abstract: A thrust reverser including a stationary structure, a lower door and an upper door. This reverser includes at least one deflector configured to be able to redirect forward from the stationary structure a portion of fluid exiting the reverser according to a trajectory oriented towards a lateral opening extending between the stationary structure and the upper door. Such a deflector makes it possible to improve the control of the air current lines acting on a tail unit and in particular on a control surface of an aircraft equipped with such a reverser when the latter is in thrust reversal configuration, thereby making it possible to improve the controllability of this aircraft.

Abstract: A connecting rod for a nacelle of a turbine engine is described. The connecting rod includes a region configured to move the center of aerodynamic forces able to be exerted on the connecting rod, in the direction of an air flow intended to be generated during a thrust generated by the turbine engine.

Abstract: A position sensor for an aircraft nacelle thrust reverser door for an aircraft turbojet engine includes a target to be detected, a detector having a detection range and including a detection head configured to detect the target when it enters its detection range, and a target guide configured to guide the target in order to position it in the detection range of the detector. The detector is stationary relative to the target guide. In one form, the target is intended to be positioned on the door, and the detector and the target guide are intended to be positioned on a stationary structure of the thrust reverser. In another form, the target is intended to be positioned on a stationary structure of the thrust reverser, and the detector and the target guide are intended to be positioned on the door.

Abstract: Disclosed is an air intake of an aircraft turbine engine nacelle having a lip, a downstream portion and an internal partition separating the lip and the downstream portion, the lip delimiting an annular recess, the downstream portion having a downstream inner wall and a downstream outer wall, the air intake having an injection channel for injecting a hot air stream into the annular recess, a passage opening formed in the internal partition, an outlet opening formed in the downstream outer wall and a discharge channel for discharging the hot air stream mounted in the downstream portion and having a first end connected to the internal partition, a second end connected to the downstream outer wall and a main body having at least one flexible portion.

Abstract: An acoustic attenuation panel includes a cellular structure including a plurality of acoustic cells separated from one another by peripheral partitions, a perforated acoustic structure, the perforated acoustic structure and the cellular structure being formed in one piece in a first material, and a porous acoustic layer formed of a second material and fastened to a surface of the perforated acoustic structure by entangling the first material and the second material.

Abstract: A nacelle for an aircraft turbojet engine includes a thrust-reversing device with a fixed structure and a movable structure translatably movable along an axis substantially parallel with a longitudinal axis of the nacelle between a retracted position in which it provides aerodynamic continuity with the fixed structure of the nacelle during operation of the nacelle with forward thrust and a deployed position in which it opens a passage intended for the circulation of a diverted secondary air flow during operation of the nacelle with reverse thrust. The nacelle includes at least one position sensor configured and arranged in the nacelle for detecting a deformation of the movable structure exceeding a permitted predetermined deformation threshold.

Abstract: An air intake of a turbojet engine nacelle includes an annular structure including an outer fairing defining an aerodynamic outer surface and an inner fairing defining an aerodynamic inner surface. The outer and inner fairings are connected upstream by an air intake lip forming a leading edge. The inner fairing includes an outer skin fixed to the air intake lip by an upstream fixation flange, and the outer skin is configured to be fixed to an outer fan casing by a downstream fixation flange. The air intake includes at least one independent acoustic panel attached to the outer skin and which includes a perforated acoustic skin and a cellular core.

Abstract: The present disclosure particularly relates to an acoustic attenuation structure for a propulsion assembly of an aircraft. The acoustic attenuation structure includes an acoustically reflective wall and a sandwich panel. The sandwich panel includes a honeycomb structure surrounded by two acoustically porous skins, a rear skin and a skin. The acoustically reflective wall and the sandwich panel are arranged in such a way as to be separated by a layer of air.

Abstract: An air intake scoop intended to be fastened on a panel of an aircraft includes an air inlet mouth having a wall, a peripheral collar intended to be fastened to the panel, and a bearing element intended to support the air circulation duct. The air inlet mouth is made of a thermoplastic material and the bearing element is fastened on the peripheral collar so as to achieve a pressure barrier in case of breakage of the wall of the air inlet mouth.

Abstract: A nacelle for an aircraft turbojet engine includes a thrust-reversing device with a fixed structure and a movable structure translatably movable along an axis substantially parallel with a longitudinal axis of the nacelle between a retracted position in which it provides aerodynamic continuity with the fixed structure of the nacelle during operation of the nacelle with forward thrust and a deployed position in which it opens a passage intended for the circulation of a diverted secondary air flow during operation of the nacelle with reverse thrust. The nacelle includes at least one position sensor configured and arranged in the nacelle for detecting a deformation of the movable structure exceeding a permitted predetermined deformation threshold.

Abstract: An aircraft turbojet engine nacelle includes a rear section without a lower bifurcation, the rear section including a thrust reverser system, and the thrust reverser system including a movable cowl. The nacelle includes a guide system including a movable portion and a fixed portion, the movable portion being secured in translation to the movable cowl and cooperating with the fixed portion and the fixed portion being fixed relative to the nacelle. The guide system is disposed proximate to a position called the “6 O'clock” position. In one form, the length of the fixed portion of the guide system is larger than or equal to 50% of the length of the movable portion.

Abstract: The present disclosure particularly relates to an acoustic attenuation structure for a propulsion assembly of an aircraft. The acoustic attenuation structure includes an acoustically reflective wall and a sandwich panel. The sandwich panel includes a honeycomb structure surrounded by two acoustically porous skins, a rear skin and a skin. The acoustically reflective wall and the sandwich panel are arranged in such a way as to be separated by a layer of air.

Abstract: The present disclosure relates to a cascade thrust reverser providing that when a sliding cowl and a flap are in a direct jet position, a hook is held in engagement with another hook and the flap is immobilized inside of a housing of the sliding cowl by a stem of a telescopic connecting rod subjected to pre-stress generated by a compressed spring located in the body of the connecting rod. When the sliding cowl starts to slide from the direct jet position toward the reverse jet position, the hooks disengage each other and the stem engages with an extension in the body of the connecting rod, so that the flap is rotated from the direct jet position toward the reverse jet position due to the tensile force exerted by the stem.