Abstract: An antenna is selected in a system including a first and at least one second device. The system forms a communication network of TDMA type where each communication occurs in frames. The first device includes plural antennas that each covers a predefined sector near the antennas. The frames are organised in a succession of groups of consecutive frames, each group being organised in a structure associating each frame with a pair formed by an antenna of the first device and of a second device, each possible pair being associated with a different frame in the group according to a position of the frame in the group. For each device including plural antennas: information is obtained representing communication quality between the device's antenna and the first or a second device's antenna, and the antenna is selected having the highest communication quality with an antenna of the first or a second device.

Abstract: Method implemented in a system comprising a control station and at least one drone. Each data communication in said system between the control station and a drone taking place in the form of packets, each packet comprising a preamble and being transmitted in a form modulated according to a predefined modulation. The method comprises: using, in each packet communication from the control station to a drone, a so-called uplink preamble, orthogonal to the so-called downlink preamble, used in each packet communication from a drone to the control station; and, on reception of a modulated packet, determining whether said modulated packet has been transmitted in the context of an uplink or downlink communication according to a result of a convolution between said modulated packet with a reference preamble modulated according to the predefined modulation, said reference preamble corresponding to the uplink preamble or to the downlink preamble.

Abstract: A multi-point fuel injection device for an aircraft engine, including an inlet line, at least two injection lines, and a purge line, a fuel distributor member connected to each line and including a moveable element which includes an injection passage, in which the moveable element additionally includes a purge passage, and is configured to adopt a first range of positions in which the injection passage interconnects the inlet line and the injection lines, and a second range of positions in which the injection passage interconnects the inlet line and at least a first injection line while the purge passage interconnects the purge line and at least a second injection line, the device additionally includes an actuator adapted to move the moveable element into a safety position when a failure of the distribution member is detected, the injection passage interconnecting, in this safety position of the moveable element, the inlet line and the first injection line while the purge passage does not interconnect the pur

Abstract: The invention relates to a method for measuring pollutants contained in an exhaust stream exiting an engine, comprising the steps consisting of: Positioning a probe such that a sampling opening of said probe is positioned on a sampling surface provided at the outlet of the engine in the exhaust stream, and sampling the exhaust stream with said probe; Activating an analysis unit coupled with the probe in order to acquire characteristic data of the exhaust stream sampled by the probe; Controlling a movement of the probe to impart a continuous movement of the sampling opening along a specific trajectory on the sampling surface with constant surface scanning per unit of time, while continuing the sampling and the acquisition of characteristic data of the exhaust stream sampled by the probe; —Processing the data acquired by the analysis unit to measure the pollutants present in the exhaust stream. The invention also relates to a device for implementing this measuring method.

Abstract: An aircraft landing gear assembly has a main strut and a bogie beam pivotally coupled to the main strut via a coupling assembly. The coupling assembly is arranged to define a bogie beam pivot axis relative to the main strut which is spaced from the landing gear assembly, and perpendicular to the direction of travel. The coupling assembly has a pair of arms, each having an upper pivotal coupling to the main strut and a respective lower pivotal coupling to the bogie beam. Each arm has a respective connection axis which intersects respective axes of its upper pivotal coupling and lower pivotal coupling. The upper pivotal couplings and lower pivotal couplings are arranged such that their connection axes intersect at a virtual pivot axis which defines the bogie beam pivot axis.

Abstract: A method is provided. The method includes, after a landing of an aircraft, detecting by sensors the position of the landing gear at a first sampling frequency, while the position of the landing gear is detected as vertical. After detection of a horizontal position of the landing gear, detecting by the sensors the position of the landing gear at least at a second sampling frequency, while the position of the landing gear is detected as horizontal. After detection of a vertical position of the landing gear, acquiring by said sensors physical parameters relating to the ageing of the landing gear, and detecting a landing of the aircraft at a third sampling frequency until a predetermined period has expired. The third frequency is greater than the second frequency, which is greater than the first frequency. Measurements relating to the ageing are stored as a function of the measured physical parameters.

Abstract: When cold and in the non-coated state, an aerodynamic profile defining an arm of a structural casing of a turbine having a central hub and a shroud is substantially identical to a nominal profile determined by Cartesian coordinates X,Y,Zadim given in Table 1, in which the coordinate Zadim is a quotient D/H where D is a distance of a point under consideration from a first reference plane P0 situated at a base of the nominal profile, and H is a height of said nominal profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to an axial direction of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: Communication system, used in a drone system, based on a communication system of the TDMA type in which the time is divided into a plurality of temporal breakdown hierarchy levels. All the hierarchy levels being suitable for complying with a plurality of constraints related to the drone system comprising a first constraint meaning that each communication between a drone and a station controlling the drone system must be compatible with a conversation audio data transmission, a second constraint meaning that the control station must be capable of controlling a predefined number of drones simultaneously and a third constraint meaning that, the drone system using transmissions by bursts, each burst must be transmitted over a stationary channel.

Abstract: Track fitting assembly having a base frame (12) comprising a pivot shaft (44) arranged so that the pivot shaft substantially aligns with an upper surface of a track when the base frame is coupled to the track and at least one pivotable insert (14) pivotally coupled to the pivot shaft.

Abstract: A safety belt is intended to be installed on an aircraft seat and includes a first part and a second part which are able to be joined together by means of a buckle to hold the passenger on the seat. The safety belt may also include a status detection system able to transmit information relating to the fastening status of the safety belt, a presence detection system able to transmit information relating to the presence of a passenger wearing the safety belt, and/or a communications module, notably wireless, able to transmit information relating to the fastening of the safety belt and/or to the presence of a passenger wearing the safety belt.

Abstract: During a stage (E0) of starting the turbine engine, the method of the invention comprises: an open-loop generating step (E10) of generating a fuel flow rate command (WF_OL) from at least one pre-established relationship; and a closed-loop monitoring step (E20-E30) of monitoring at least one operating parameter of the turbine engine selected from: a rate of acceleration (dN2/dt) of a compressor of the turbine engine; and a temperature (EGT) at the outlet from a turbine of the turbine engine; this monitoring step comprising maintaining (E30) the operating parameter in a determined range of values by using at least one corrector network (R1, R2, R3) associated with the parameter and suitable for delivering a signal for correcting the open-loop generated fuel flow rate command so as to maintain the operating parameter in the determined range of values.

Abstract: A nickel-based superalloy comprises in mass percent: 4.0% to 6.0% chromium; 0.4% to 0.8% molybdenum; 2.5% to 3.5% rhenium; 6.2% to 6.6% tungsten; 5.2% to 5.7% aluminum; 0.0 to 1.6% titanium; 6.0% to 9.9% tantalum; 0.0 to 0.7% hafnium; and 0.0 to 0.3% silicon; the balance being constituted by nickel and any impurities. A monocrystalline blade comprises such an alloy and a turbomachine including such a blade.

Abstract: Passenger seats having improved comfort emergency egress solutions for mini suites or other types of passenger seats that have a privacy screen, wall, or sliding door that divides the passenger seat from the aisle area or other common area. Specific embodiments find particular use on-board passenger transportation vehicles, such as aircraft, where comfort and privacy must be balanced with safety and federal regulations.

Abstract: This device for connecting conductors, in particular electrical conductor cables or optical fibres, comprises a hollow body (3) defining an inner passage (P) for the conductors and an attachment member (5) for attaching the body onto a connector (4). The device comprises a removable spacer (6) that can be positioned in the extension of the body, between the body and the connector, the spacer internally defining a chamber opening on either side of the spacer at mutually opposite faces and intended to interact with the hollow body and/or the connector, the spacer being able to be opened in such a way as to allow access to the chamber.

Abstract: A method for simulating the distribution of blades on a turbomachine disc, including providing blade configurations, each being associated with a blade and including at least one measurement of a balancing parameter measured on the associated blade, search for and selection of a bladed-disc distribution combining the configurations of blades supplied with positions on the disc, the bladed disc distribution encouraging the attainment of at least one criterion defined according to a predetermined cost function dependent on the balancing parameter measurements, the search and selection being performed by successive iterations.

Abstract: A nacelle for an aircraft turbofan includes a rear section including a thrust reversal device having an upper door and a lower door, the upper and lower doors being mobile in rotation between a stowed position in which they are aerodynamically continuous with the rest of the nacelle and a deployed position in which the upper and lower doors are able to redirect forward the core and bypass flows produced by the jet engine, each door being moved from one position to the other by at least one dedicated actuator. The opening angle (X) of the upper door in the deployed position is smaller than the opening angle (Y) of the lower door.

Abstract: A control ring for a stage of variable-pitch vanes for a turbine engine includes at least one member for bearing on a casing and means for fixing the member. The member includes a bushing with an axial bore for the passage of the member or an element for supporting the member. A through-slot opens into the bore and allows for substantial radial deformation of the bushing. The member further includes an outer thread for screwing the bushing into a complementary thread of a hole in the body, thereby deforming the bushing. The member or support can be mounted and moved inside the bore, to a second position, in which the bushing is radially constrained and is tightly mounted on the member or support, which is thus immobilized in relation to the bushing.

Abstract: The invention relates to a bladed when (23) of a turbomachine (10), comprising a disk (25) that extends about a longitudinal axis (26) in a central plane (PM), and a plurality of blades (30) that are distributed at regular intervals about said longitudinal axis (26) and extend radially from the disk (25), the disk (25) being provided with a web (27) that is alternately cursed upwards and downwards relative to the central plane (PM) such that the bladed wheel (23) is deliberately mistuned.

Abstract: An aircraft undercarriage including electrical equipment (2, 3) fastened to a portion (1) of the undercarriage and a lightning protection device (10) comprising at least one shield fastened to said portion (1) of the undercarriage by fastener means so as to extend in register with the electrical equipment (2, 3) in a position that is spaced apart therefrom, the shield comprising at least a first plate (11) made of electrically conductive material that is arranged to absorb a major portion of the heat energy that is generated by the passage of a lightning wave and to discharge the electric charge of the lightning wave. An aircraft fitted with such an undercarriage.

Abstract: A turboprop including a propeller shaft and a gas generator running along this propeller shaft, this gas generator including a high-pressure shaft and a hollow low-pressure shaft both extending along the same longitudinal axis, the low-pressure shaft having a rear end coupled to a rear end of the propeller shaft via a reducer. It includes an accessory box contiguous to the reducer while being located facing a rear end of the low-pressure shaft, and coupled to the rear end of the high-pressure shaft by a shaft passing through the low-pressure shaft.