Abstract: Disclosed is a decision assistance system (8) for firing a projectile at a target (4) mounted on a mobile carrier (1), the system comprising: a first simulator (10) for applying a process repeatedly to simulated data that represent a configuration of the carrier and a trajectory of the carrier between a first (T1) and a second (T2) instant, to develop a precision of a navigation solution of the associated carrier at the second instant (T2); a second simulator (12) for: a) being initialized with said precision, b) applying a process repeatedly to simulated data that represent a trajectory of the projectile between the second and a third instant (T3), in order to develop a precision of a navigation solution of the projectile (4) associated with the third instant (T3), and a selector (14) for either selecting the projectile or not (4) in order to fire on the target, according to the precision developed in step b).

Abstract: An abradable member for a turbomachine turbine, including a cellular structure including walls defining wells which open through a wear face. The cellular structure includes at least one flow straightener jutting from the wear face.

Abstract: An electric propulsion architecture for a multi-rotor vertical take-off and landing aircraft includes four electric generators; and four pairs of rotors. For each rotor, a first electric motor is configured to operate in an active mode, and a second electric motor is configured to be in a standby mode and being able to operate in an active mode in a breakdown situation. A propeller is coupled to the electric motors, wherein, for each pair of rotors, one of the electric generators powers the first electric motors, and another of the electric generators powers the second electric motors. The rotors form counter-rotors, and for each counter-rotor, the electric motors are each powered by one of the four electric generators so that the four electric generators power the electric motors of the rotors of each counter-rotor.

Abstract: A method for monitoring an aircraft component, including the following steps: receiving, from a video acquisition device, a video stream that represents at least one portion of the component; in the event that the realization of a predetermined condition is detected, extracting a portion of the video stream to form a sequence of interest; identifying, within the extracted sequence of interest, at least one image of interest; including a signature, obtained using each image of interest, with at least one predetermined signature from a library of signatures; and generating an anomaly detection signal if the result of the comparison meets a predetermined criterion.

Abstract: Propulsion assembly for an aircraft, comprising a fuselage extending along a longitudinal axis and enclosing an inner enclosure, at least one ducted engine fixed to the fuselage and comprising an air inlet section, the air inlet section being disposed at least partly in the inner enclosure, at least one plenum chamber disposed in the inner enclosure upstream of the air inlet section and in fluid communication with said air inlet section, at least one air intake formed on an outer wall of the fuselage, the inlet of the air intake being partly delimited by said outer wall of the fuselage, the air intake being configured to ingest external air and deflect it towards the plenum chamber.

Abstract: An abradable structure (36) is provided, with regions (44, 45, 46) with lower resistance to wearing produced by labyrinth seal lips (4, 5), at specific points in the axial direction of the turbomachine, where lip interference could cause the rotor to block up, such as after a temporary shutdown of the turbomachine. These regions may be produced by local weakening (38) or by the abradable material having a structure that is less dense. Application, for example, to turbomachine turbines.

Abstract: A grid-type thrust reverser for a turbojet engine includes a moving O-shaped thrust reverser body that is generally cylindrical in shape around a longitudinal central axis (A) and includes an inner wall configured to delimit a cold air stream, with an inner structure that surrounds the turbojet engine, the movable thrust reverser body being mounted so as to be able to slide along the longitudinal central axis (A) between a direct jet position in which the outer cowl covers the thrust reverser grids, and a thrust-reversal position in which the outer cowl uncovers the thrust reverser grids. The movable thrust reverser body includes a first half-portion and a second half-portion that are mounted so as to each pivot about a longitudinal pivot axis (B), between a closed position and an open gullwing position for removing the turbojet engine, via the cradle.

Abstract: A switching circuit comprising a transistor (23) and a drive component both for controlling the transistor and also for limiting the power supply current (Ia) suppled to a load (22), the drive component being arranged both to receive a control voltage (VH) and also: when the control voltage (VH) is disconnection signal, to generate a drive voltage (Vp) that causes the transistor to occupy a non-conductive state; when the control voltage (VH) is a connection signal and the power supply current (Ia) cannot reach a predefined current threshold, to generate drive voltage (Vp) that causes the transistor to occupy saturated conditions; and when the control voltage (VH) is a connection signal and the power supply current (Ia) can reach a predefined current threshold, to generate a drive voltage (Vp) that causes the transistor to occupy linear conditions, such that the power supply current is regulated so that it does not exceed the predefined current threshold.

Abstract: A turbomachine module with a longitudinal axis, the module comprising: a rotary casing rotatable around the longitudinal axis and arranged to carry a propeller provided with a plurality of blades; a system for changing the pitch of the blades of the propeller comprising: a control, and a mechanism for varying the pitch of the blades of the propeller connecting these blades to the control, wherein the control comprises a rotary actuator comprising a control body and a reference body which is integral with the rotary casing, and wherein the mechanism for varying the pitch comprises a synchronization ring which is driven in rotation around the longitudinal axis by the control body and which is guided in rotation on the rotary casing, the synchronization ring being connected to the blades.

Abstract: The present invention concerns a mounting structure and arrangement. More particularly, but not exclusively, this invention concerns a mounting structure and arrangement for mounting aircraft furniture in an aircraft. The mounting structure comprises a first connection assembly configured for engagement with a first mounting track; and an associated first support. The first support is configured to abut the first mounting track at a location fore or aft of the first connection assembly. The provision of the support may reduce the number of connection assemblies required to properly secure an item of aircraft furniture in an aircraft cabin using the mounting structure.

Abstract: Described are aircraft cabin arrangements (12) with at least one lavatory unit (14) with a first side wall (1402) and at least one seat unit (16) positioned adjacent the first side wall. A separate wall is not positioned between the first side wall and the at least one seat unit. The first side wall includes a recessed portion, and the at least one seat unit includes a foot support surface (1606) incorporated into the recessed portion of the first side wall.

Abstract: The invention provides an engagement method for engaging a first gear element with a second gear element, at least the second gear element being mounted to move between a meshing position and a disengaged position by means of an actuator. The engagement method including a step of driving at least one of the gear elements in rotation so as to establish a non-zero difference in speed of rotation between said gear elements, and a step of controlling the actuator to perform the following in succession: moving at least the second gear element towards the meshing position; on detecting contact between the gear elements, stopping the movement of the second gear element; and on detecting an ideal angular position for engaging said gear elements, moving the second gear element as quickly as possible into the meshing position.

Abstract: A turbine blade for a turbomachine includes a turbine blade with a leading edge and a trailing edge. The blade includes a radially outer platform with at least one lip extending radially towards the outside. The radially outer end of the leading edge and/or of the trailing edge of the turbine blade airfoil extending axially upstream and/or downstream, respectively, in relation to the platform. The blade has at least one partition extending radially towards the outside from the radially outer end of the turbine blade airfoil and axially between the leading edge and the upstream end of the platform and/or between the trailing edge and the downstream end of the platform.

Abstract: The present disclosure relates to a cell structure for an acoustic attenuation device for a nacelle of an aircraft propulsion assembly. This cell structure includes lateral partitions forming channels that each extend between a first end and a second end and skin elements arranged so that each channel is at least partly closed at the first end thereof by at least one skin element. Each skin element is connected to a respective lateral partition and can move relative to the other lateral partitions. A continuous skin can be assembled on this cell structure so as to at least partly close the channels at the second end thereof and to thus form an acoustic attenuation device.

Abstract: A cooling device for an annular casing of a turbomachine includes a collector housing having ejection openings in a radially inner part of the collector housing facing the annular casing and at least two cooling tubes extending circumferentially from the collector housing and having election openings in a radially inner part of the tubes facing the annular casing. The collector housing having an air passage formed by a radial groove extending radially from a radially inner end of the collector housing to a radially outer end of the collector housing and an axial groove extending from a first axial end to a second axial end of the collector housing.

Abstract: A production method of a maraging steel includes: the step of producing, by vacuum melting, a remelt electrode which comprises from 0.2 to 3.0% by mass of Ti and from 0.0025 to 0.0050% by mass of N; and the step of remelting the remelt electrode to produce a steel ingot having an average diameter of 650 mm or more; wherein the resulting maraging steel includes from 0.2 to 3.0% by mass of Ti.

Abstract: An annular heat exchanger with a longitudinal axis for a turbomachine, intended for example to be supported by an annular shell of a casing of the turbomachine, includes a one-piece annular part having a first fluidic circuit having at least one first conduit and at least one second conduit extending annularly and a second fluidic circuit having at least one first conduit and at least one second conduit extending annularly and arranged in a direction perpendicular to the longitudinal direction on either side of the first conduit and second conduit of the first circuit.

Abstract: A landing gear includes structural parts arranged to connect a wheel to a structure of an aircraft, each structural part including two or more interfaces for connection to one or more other of the structural parts or to the structure of the aircraft and two or more webs which extend so as to face one another while delimiting between them a free space and which connect the two interfaces in order to transmit the forces from one to the other.

Abstract: A metal core for hot-forming a titanium-based alloy metal component is disclosed. The metal core has on an outer surface, intended to come into contact with the metal component, a layer of metal carbonitride-enriched material. The metal core comprises a nickel- or cobalt-based alloy. The metal core comprising a steel coating having an outer surface intended to come into contact with the metal component, the steel coating having a layer of metal carbonitride-enriched material. Processes for manufacturing and regenerating the metal core and a process for hot-forming a metal component using the metal core are also disclosed.

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.