Abstract: The present disclosure provides an iterative method for draping fiber plies to produce a preform for a composite wall with an organic matrix. The method comprises the sequential stacking of woven fiber plies on a template. The plies are covered with reference markings, particularly with tracer threads forming a grid pattern, the positions of the threads being indicated by means of illuminated marks projected by a laser. The reference markings of the plies are moved in turn until they coincide with their corresponding marks, thereby ensuring the correct positioning of the corresponding ply. The stack contains plies with threads orientated at ?45°/+45° and at 0°/90°. The illuminated marks change with each type of ply so as to project dedicated indications onto the plies. The present disclosure also provides a draping installation and a composite wall of a casing of an axial turbine engine, or of a motor vehicle structure.

Abstract: The invention relates to a suspension pylon comprising: at least one arm (3) for suspending a propulsion unit (4) from the fuselage (2) of an airplane (1), an oil exchange circuit (70) configured to be connected, on the one hand, to an oil pump (5) in the fuselage (2) and on the other hand, to the propulsion unit (4) the arm (3) whereof provides for suspension, said circuit (70) comprising a feed line (72) and a return line (74), which both extend inside said arm (3), an intermediate shaft (6) which extends in said arm (3), said shaft being configured, on the one hand, to be driven by the propulsion unit (4) the arm (3) whereof provides for suspension and, on the other hand, to drive the oil pump (5) in the fuselage (2), wherein the arm (3) has a structure adapted for cooling the oil exchange circuit at the arm (3).

Abstract: The invention relates to a lubrication device for a turbine engine, comprising an oil intake pipe (23) provided with a pump (24) for supplying oil and control means (30) located downstream from the supply pump (24), a supply pipe (26) intended for supplying oil to a member to be lubricated and a recirculation pipe (27) connected upstream from the supply pump (24), the control means (30) making it possible to direct all or part of the flow of oil from the intake pipe (23) towards the supply pipe (26) and/or towards the recirculation pipe (27).

Abstract: The invention relates to tooling (24) for machining an annular groove of a turbine engine casing, wherein said tooling (24) comprises a machining tool (25), a baseplate (33), first means of positioning (28) the machining tool (25) in relation to the baseplate (33) along a first axis (Y) forming a radial axis, second means of positioning (30) the machining tool (25) in relation to the baseplate (33) along a second axis (X) perpendicular to the first axis (Y), wherein said second axis (X) extends along the axis of the groove and of the annular casing and third means of positioning capable of positioning the baseplate (33) axially and radially in relation to the groove of the casing.

Abstract: A compressor shroud for an aircraft turbine engine, the shroud being arranged between two bladed rotary wheels and radially in line with a deflector, the shroud including a sealing device including one or more sealing elements, including a downstream end sealing element on which, projecting downstream, an air entraining and diverting structure is provided, designed to axially divert the discharge air issuing from the end sealing element.

Abstract: The invention relates to a nacelle (1) for an aircraft turbojet, the nacelle comprising a frustoconical radially outer annular wall (13), a pylon (9) extending radially outwards from said annular wall, the pylon (9) being designed to fasten the nacelle (1) to a fixed portion of the airplane, said nacelle being characterized in that it is provided with at least one projecting zone (22) extending radially outwards from the frustoconical outer wall (13), said projecting zone (22) being situated in the vicinity of a downstream annular edge (14) of said outer wall (13) and in the vicinity of the pylon (9).

Abstract: The invention relates to a fairing (37) for a mixer (28) of a nozzle (26) of a dual-flow turbomachine (20), said mixer being of an overall annular shape and extending along a longitudinal axis (24) of the turbomachine, said mixer comprising an upstream part (29) provided with a flange (31) extending radially toward the outside of the mixer, intended to be fastened to an exhaust casing (21) of the turbomachine, and a downstream part (33) forming a flow mixing area, the fairing (37) being of an overall annular shape and configured to extend around the upstream part (29) of the mixer (28) and to be attached to the flange (31) of said upstream part (29), the fairing being without means for fastening to the downstream part (33) of the mixer (28), in such a way as to connect the fairing (37) to the mixer (28) at a distance from the flow mixing area.

Abstract: A monitoring system for monitoring a piece of aircraft equipment, the system comprising a master electronic module and a slave electronic module, each fitted with first wireless communication means, the slave electronic module further comprising measurement means for the purpose of taking measurements of a parameter of the aircraft equipment, and power supply means making the slave electronic module independent in terms of energy, the master electronic module further comprising detector means adapted to detect a stage of flight in which the aircraft is to be found, and control means for acting via the first wireless communication means to control the measurement means of the slave electronic module so as to adapt the measurements taken by the measurement means to the detected stage of flight.

Abstract: The invention relates to a blade (16), in particular a fan blade, for resurfacing an abradable coating (26) on an internal surface of a turbine engine case (18) intended to surround the blade. The comprises a root (20) and an airfoil (24) having a tip opposite the root, said root comprising a housing (32) for the storage or passage of a polymerisable refill resin. The airfoil comprises longitudinal channels (34), the first ends of said channels being connected to the housing and the opposite ends opening at the aforementioned tip.

Abstract: A method of regulating a temperature (TM) associated with a heat exchanger assembly (10) of a turbine engine (1), the method comprising, in a single cycle: measuring (500) the temperature (TM) of an air stream at the outlet from a heat exchanger (14); receiving a setpoint temperature (TC) for the air stream at the outlet from the heat exchanger (14); estimating (510) a theoretical temperature (TT) for the air stream at the outlet from the heat exchanger (14) as a function of an estimate of the position of a shutter of a controlled valve (15) bleeding off a cooling air stream for the heat exchanger (14); determining a correction current (ICO) from the difference (?T1) between the measured temperature (TM) and the theoretical temperature (TT); and determining (530) a control current (IC) for the shutter from the difference (?T2) between the measured temperature (TM) and the setpoint temperature (TC) and while taking account of the correction current (ICO) determined during the preceding cycle, the position of t

Abstract: Described is a breakover mechanism for a passenger seat that includes a frame member with a rear portion attached to two opposing sides of a seat back of the passenger seat wherein the frame member is at least partially disposed under a seat pan of the passenger seat, at least one moving portion attached to a forward portion of the frame member, a carriage portion fixedly attached to the seat pan; and a single point mechanism attached to the carriage portion. Once a threshold loading condition occurs, the single point mechanism changes states to facilitate movement of the moving portion relative to the carriage portion.

Abstract: A pitch actuation system for a turbomachine propeller, comprising an actuator with a movable portion configured to be connected to blades of the propeller in order to rotate them relative to the blade-pitch setting axes, wherein the actuator is an electromechanical actuator and comprises: blade-pitch control having a transmission screw rotated about an axis; a nut through which said transmission screw passes; and a member configured to engage with the blades in order to move the blades, wherein the nut is connected to the member via a decoupler configured such that a translational movement of the nut causes a translational movement of the member, but rotational movement of the member does not cause rotational movement of the nut.

Abstract: The invention relates to a bar spacer (10) for a braked aircraft wheel, the bar being for fitting to a rim (1) of the wheel in order to drive the rotor disks of the brake in rotation, the spacer being for interposing between the bar and the rim, the spacer comprising two bearing blocks (11) connected together by a core (15) that is pierced to pass a screw for fastening the bar to the rim. According to the invention, the bearing blocks (11) of the spacer include voids defining a void fraction of at least 30% of the volume of the bearing blocks.

Abstract: The invention relates to an aircraft landing gear (2) comprising:—a leg (6) having a first leg portion (8) that can be pivotably connected to a load-bearing structure of the aircraft (1) in order for the landing gear (2) to be deployed and retracted, and a second leg portion (9) that is rotatable in relation to the first leg portion (8);—a wheel (13, 14) that is rotatable in relation to the second leg portion (9), and an electric motor (15, 16) that can rotate the wheel (13, 14) in relation to the second leg portion (9);—a transmission mechanism (17) designed to selectively transmit torque generated by the electric motor (15, 16) to the wheel (13, 14) in order to rotate the wheel in relation to the second leg portion (9) or to the second leg portion (9) in order to rotate the second leg portion (9) in relation to the first leg portion (8).

Abstract: The present invention relates to a method (100) for intentionally mistuning a turbine blade of a turbomachine (10), by providing raised portions (31) or slots (32), the position of which is calculated on the basis of a vibration analysis of the disk (steps a) to d)).

Abstract: A method for controlling an aircraft taxiing system, comprising the steps of: generating a nominal load command (Comm_nom); generating an acceleration setpoint (Cons_a); implementing, in parallel with the generation of the nominal load command, a processing chain (7) comprising a regulation loop (Br), the regulation loop (Br) having for its setpoint the acceleration setpoint (Cons_a) and for its command an acceleration command (Comm_a), the acceleration command being converted into an acceleration load (Eff_a), a maximum load threshold being equal to the maximum of the acceleration load (Eff_a) and a minimum load threshold (Seuil_min); and generating an optimized load command (Comm_opt) equal to the minimum of the nominal load command and the maximum load threshold.

Abstract: The invention relates to a system (2) for generating non-propulsive energy in an aircraft, including: an auxiliary power unit (20) including a gas turbine (21) and a fuel cell (22); a pathway (23) for the intake of outside air into the aircraft; an exhaust pipe (24) of the gas turbine, the system being characterized in that the air intake pathway (23) includes a pipe (230) for cooling the fuel pipe, in that the pipe is in fluid communication with the exhaust pipe (24) of the gas turbine such that the ejection of the gas from the gas turbine into the exhaust pipe causes a suction of the air outside the aircraft into the cooling pipe (230) by Venturi effect. The invention also relates to a method for generating non-propulsive energy.

Abstract: An electric motor stator wherein an annular central part and a yoke surrounding the central part, the central part includes a bundle of laminations delimiting poles, wherein the bundle of laminations includes a plurality of first laminations each containing portions forming a pole part that are joined by an annular internal portion, second laminations each forming a pole part being mounted between the first laminations, the first laminations being spaced apart from one another at a predetermined spacing according to a required inductance.

Abstract: An obtaining step for obtaining a measurement of the monitored parameter as measured by a sensor and corresponding to an operating point of the engine, the operating point being defined by at least one regulation parameter of the engine; an estimation step for estimating a value of the monitored parameter for this operating point on the basis of a regulated value or a filtered setpoint value of the at least one regulation parameter of the engine defining the operating point; a comparison step for comparing an error between the measurement of the monitored parameter and its estimate relative to at least one threshold determined on the basis of an uncertainty on the error evaluated for the operating point; and a notification step for sending a notification in the event of the at least one threshold being crossed.

Abstract: The present disclosure relates to a method of controlling the braking of an aircraft equipped with a landing gear bearing braked wheels, the aircraft being propelled by jet engines and equipped with a thrust reversal system, the method involving the steps of estimating the grip/adhesion of the braked wheels and activating the thrust-reversal system or modulating the reverse-thrust generated by the thrust-reversal system if this system is already activated, based on the estimated grip/adhesion.