Abstract: An actuation device for a thrust reverser includes thrust-reversal movable elements carried by a nacelle and displaceable between a retracted and deployed position. The actuating device includes two actuators mounted on the nacelle and connected to a motor and to the movable elements. The actuation device drives the movable elements in a retraction or deployment direction over a course of the actuators between the retracted and deployed position. The actuation device further includes locks for locking the movable elements in the retracted position and antideployment members associated with the actuators which allow free operation of the actuators in the direction of retraction and retain the actuators in the direction of deployment. The antideployment bodies further provide free operation of the actuators in the direction of deployment over part of the actuators stroke that corresponds to a shift from an over-retraction position to the retraction position of the movable elements.

Abstract: An aircraft undercarriage (0) comprising: a wheel (R); a support (2); a drive system (1) for driving rotation of the wheel, the drive system being mounted to move relative to said support (2) between an engaged position and a disengaged position; a mover system (3) for moving the drive system (1) between its positions; a first pair of links (51, 52) hinged to each other about a first hinge axis (X1) to pivot during the movement of the drive system between its engaged and disengaged positions; and a locking actuator (V) and at least one first target (V1), the locking actuator (V) acting on the first target (V1) to lock or unlock the drive system (1) and the first target (V1) being carried by one of the links (52).

Abstract: The invention provides a communications network comprising at least two modules and a common switch connected firstly to the two modules and secondly to various different user terminals, the switch having as many configurations as there are user terminals and modules connected to the switch, each user terminal and each module being associated with a particular dedicated configuration.

Abstract: A state monitor for monitoring the state of a system and including a calculator and a memory; the system being controlled by a command defining a plurality of modes of operation of the system, each mode of operation corresponding to applying a command of constant value; the memory containing a set of stored state matrices representing, for each mode of operation of the system, the value of the projection of its state in time; and the calculator being configured, during operation of the system, to determine estimated values for the state of the system at a given instant with the state functions and of its state at an earlier instant.

Abstract: An annular air flow passage includes two radially internal and external annular walls. An element is elongated in a direction between the internal and external annular walls and a first of the internal or external ends of the element is fixed rigidly to a first of the internal or external walls. The center of gravity position of the element is variable.

Abstract: A method of monitoring the opening of a container, the method comprising the steps of: putting a monitoring device into a closed mode of operation (11) when detection means detect that the container is closed, in which mode a communications module sends closed messages at a first status repetition rate; when the detection means detect that the container is open, putting the monitoring device into a warning mode of operation (12) in which the communications module sends open messages at a second status repetition rate; and when the monitoring device is in the warning mode of operation (12) and the communications module receives an opening validated message, putting the monitoring device in an opening validated mode of operation (13) in which the communications module sends open messages at a third status repetition rate.

Abstract: The invention relates to a method for monitoring the soundness of helicopters comprising the determination of the severity of a plurality of flight missions of a plurality of helicopters, comprising a step for acquiring and storing flight data from helicopter flight missions, and a step for acquiring and storing maintenance data from the plurality of helicopters. The method is characterised in that said determination comprises a mission-type construction step, comprising a sub-step for constructing descriptors, a sub-step for partitioning the descriptors and a sub-step for allocating a mission type to each flight by associating the descriptor of said flight and a sub-set, in which this descriptor is found, and a step for interpreting the severity of the mission types, comprising a sub-step for estimating the severity models, and a sub-step for associating a severity model with each mission type determined in the mission type construction step.

Abstract: A turbomachine fuel circuit including: a low pressure pump; a high pressure pump; a low pressure conduit connecting the low pressure pump to the high pressure pump; a high pressure conduit supplied by the high pressure pump, in which a component is arranged; a mechanism for testing operation of the component; a check valve capable of closing off a segment of the conduit when the pressure in the low pressure conduit is less than a predetermined threshold value; and the testing mechanism is capable of detecting that the check valve at least partly closes off the segment.

Abstract: The invention concerns a method for controlling the integrity of the value of a piece of navigation information delivered by a merging/consolidation device including a plurality of processing modules. Each module generates a navigation solution from measurements coming from one or a plurality of separate navigation devices, which involves defining, for each processing module, a radius of protection, corresponding to a given probability of failure. The method includes defining at least one consolidated area that encompasses protection areas centered on the solution values that are output from the processing modules and that correspond to the radii of protection defined for these modules. The radius of protection of the merging/consolidation device for the probability of failure itself is defined to correspond to the consolidated area.

Abstract: A method of moving a door of a well for an aircraft undercarriage during sequences of deploying or retracting the undercarriage includes: using a temporary mechanical connection between the door and the undercarriage that is effective when the undercarriage is close to its retracted position, causing the door to be opened by the undercarriage while the undercarriage is being deployed and causing the door to be closed by the undercarriage while the undercarriage is being retracted, but releasing the door from the undercarriage when the undercarriage is close to its deployed position, and using a door actuator acting on the door to close and open the door when the undercarriage is in its deployed position and the temporary mechanical connection is interrupted.

Abstract: An onboard system and a method for draining an aeroengine. The onboard system comprises a buffer tank having an admission passage for admitting under gravity fluid coming from the aeroengine, a primary tank situated above the buffer tank and having an emptying passage for emptying the fluid coming from the aeroengine, and a lift circuit connecting the buffer tank to the primary tank in order to transfer the fluid coming from the aeroengine from the buffer tank to the primary tank.

Abstract: The invention relates to a temperature measurement device comprising at least three probes, a computer, the computer being configured to estimate a temperature on the basis of voltage measurements at the output of the probes, characterised in that the probes are connected together in a plurality of meshes mounted in series, with at least one mesh comprising at least two probes mounted in parallel and at least one other mesh comprising a probe or a plurality of probes mounted in parallel.

Abstract: Generally described, a hybrid additive manufacturing method may be used to produce complex parts using additive manufacturing technologies. The methods may include manufacturing one or more first portions of the part with a first additive manufacturing process, such as a powder bed fusion process using a metallic powder source material. The first portion of the part is then transferred to an operating bed of a second additive manufacturing process, such as a direct deposition process using a solid metallic source material. In this regard, the first additive manufacturing process is different from the second additive manufacturing process. Next, another portion of the part is manufactured, coupled to, and partially surrounding the first portion of the part using the second additive manufacturing process, portions of which may be machined with a tool to provide a finished part.

Abstract: The invention relates to an electrical transformer (T, T?) comprising: a primary central winding (11a) extending around an axis (X) and configured to generate a central magnetic flux when a current is passed through it circulating in a first direction around the axis (X), two peripheral primary windings (12a, 13a) extending around the axis (X), between which the central primary winding (11a) is located, and configured to generate peripheral magnetic fluxes when currents are passed through same respectively circulating in a second direction around the axis (X) which is opposite to the first direction, the peripheral magnetic fluxes superimposing on the central magnetic flux, wherein the windings are further configured in such a way that the peripheral magnetic fluxes compensate the central magnetic flux in the regions located beyond the peripheral windings.

Abstract: A fiber preform for a turbine engine blade, the preform comprising a main fiber structure (40) obtained by a single piece of three-dimensional weaving, said main first structure (40) comprising a first longitudinal segment (41) suitable for forming a blade root, a second longitudinal segment (42) extending the first longitudinal segment (41) and suitable for forming an airfoil portion (22), and a first transverse segment (51) extending transversely from the junction (49) between the first and second longitudinal segments (41, 42) and suitable for forming a first tongue for a first platform, wherein the first transverse segment (51) extends axially over a length that is less than 30%, preferably less than 15%, of the length of the junction (49) between the first and second longitudinal segments (41, 42).

Abstract: A mechanical decoupler (15) at the inlet to a turbomachine is positioned on the outside of an intake casing, where radiating arms (27) meet an external casing (13) so as to partially unload a low-pressure shaft when a significant out-of-balance appears. Because it is positioned a long way from the bearing, the decoupler (15) can be designed with a greater degree of freedom at a location where there is more space available and where layout constraints are less of an issue. More specifically, it is housed in a cavity (30) of the external casing (13) which opens onto the flow path (5).

Abstract: The invention relates to an observation device having a location determination functionality for the high-accuracy determination of the spatial location and thus the position and orientation (for example, Euler angles: azimuth, elevation angle, and roll angle) of the observation device by analysis of a recorded camera image of the terrain surrounding the camera by means of the three-dimensional map information of a digital terrain model (DTM). For this purpose, the observation device comprises a camera having an objective lens and a camera sensor, a data memory, a sensor system, an analysis unit, and a display screen.

Abstract: A turbine ring assembly including a ring support structure and a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring, each sector presenting in a first section plane defined by an axial direction and a radial direction of the ring a portion forming an annular base having, in the radial direction, an inner face and an outer face from which there extend two attachment tabs defining between them a circumferentially-open annular cavity, the structure including two radial tabs between which the attachment tabs are held, and at least one injection orifice for injecting a stream of cooling air into the annular cavity. In a second section plane containing the axial direction and a direction orthogonal to the first section plane, the orifice forms a first feed angle relative to the direction orthogonal to the first section plane, the first feed angle lying in the range ?80° to +80°.

Abstract: A method for monitoring at least one engine of an aircraft wherein the aircraft includes a passenger cabin. The method includes a step of acquiring a signal that is at least in part representative of the activity of the engine, using a sensor during a flight of the aircraft, and searching for a defect in the engine by a processing unit using data obtained from the signal. In some embodiments, the sensor is in a mobile device located in the passenger cabin. In some embodiments, the health of the at least one engine uses the signal acquired by a plurality of mobile devices.

Abstract: A turbine engine assembly includes a housing and a bladed wheel rotatable within the housing. The bladed wheel includes a blade including a head opposite the housing. The head includes a magnet and the housing includes first and second electrical conductors. Each electrical conductor generates, across terminals thereof, an electrical voltage induced by the magnet of the head opposite the housing and that represents vibrations of the head of the blade when the bladed wheel is rotated. The first electrical conductor includes a first central portion extending around the rotational axis of the bladed wheel and includes two mutually facing ends, and the second electrical conductor includes a second central portion passing through a space left by the first central portion between the two ends thereof. The arrangement of the electrical conductors makes it possible to obtain two voltages for determining an axial vibration speed at the tip.