Abstract: A computer system is provided for processing ultrasonic data of an ultrasonic probe applied to an area of an aircraft component that includes carbon fiber reinforced polymer. C-scan data is obtained and a preliminary mesh is defined over the C-scan data by taking into account the underlying structural or mechanical characteristics of the analyzed component. The mesh is further refined and data gathered for each mesh cell. A heat map is generated based on the mesh.

Abstract: A flight management assembly of an aircraft and method of monitoring the flight management assembly. The assembly includes two flight management systems, and a monitoring and backup unit, each of the flight management systems configured for generating data including a trajectory and a prediction of a parameter of the aircraft, one of the flight management systems being active and the other being passive, the monitoring and backup unit configured for carrying out monitoring of at least one of the items of data generated by the active flight management system in order to verify if the item of data is valid, the flight management assembly carrying out, in case of validation of the monitored item of data, a synchronization of the monitoring and backup unit and of the passive flight management system, with data called synchronization data of the active flight management system, namely a flight plan and/or a flight trajectory.

Abstract: A propulsion assembly including a turbomachine attached to a pylon, and a fire-fighting system, the turbomachine including fire zones, the fire-fighting system including two reservoirs of pressurized extinguishing agent in the pylon and a distribution line connecting the reservoirs to nozzles. The distribution line includes connected pipes having a low point between the reservoirs and the nozzles, and, for each low point, a fluid drainage device for evacuating fluid. The drainage device includes a fluid passage for fluid evacuation from the distribution line and a mechanism for shutting off the fluid passage, the mechanism movable under effect of distribution line pressure, between a first position where it opens the fluid passage and a second position where it closes the fluid passage, the second position being reached when the pressure in the distribution line is greater than or equal to a predetermined pressure.

Abstract: An assembly of an engine with a pylon, including a force reacting assembly having a connection device and two rods, the connection device including a shoe. A spreader extends between first and second ends and has a central part connected to the shoe by a main connection including a main rotation pin and axis in a plane of symmetry of the connection device. Two fittings are on either side of the plane of symmetry each having two arms between which the spreader is positioned. A first, respectively second, rod includes a front end fastened to the engine and a rear end fastened to the first, respectively second, end of the spreader and to the first, respectively second, fitting by a secondary connection. Two extensions of the spreader are each associated with a pair of elastic stops. For the first, respectively second, end of the spreader, each stop is between an arm of the first, respectively second, fitting and the extension.

Abstract: The measuring device includes a substrate intended to be arranged on an aerodynamic surface; a profiled element connected at one of its ends to the substrate, and configured to be oriented, under the effect of the fluid flow; a magnet that is secured to the profiled element and is configured to generate a magnetic field; and a measuring element that is configured to measure a value of the magnetic field and to convert this measured value of the magnetic field into an angle value indicating the direction of the fluid flow; the measuring device thus making it possible to measure and provide, in real-time, a numerical angle value with which it is possible to define with high precision the direction of the fluid flow relative to the aerodynamic surface.

Abstract: An antenna arrangement for an aircraftincludes an antenna unit, a radome structure covering the antenna unit, and a mounting device for mounting the antenna arrangement to an outer surface of an aircraft component. The antenna unit is mounted to or integrally formed with the radome structure and the radome structure is mounted to or integrally formed with the mounting device.

Abstract: A propulsion assembly for an aircraft includes a pylon, a turbofan including a structure fixed to the pylon, and at least one thrust reverser, each having a top beam extending parallel to a longitudinal direction and mobile in rotation on the structure around a rotation axis parallel to the longitudinal direction. For each thrust reverser, an actuator is provided, a first end of which is articulated on the pylon and a second end of which is articulated on the top beam of the thrust reverser and the articulation axis of the actuator on the top beam is not coaxial with the rotation axis. Such assembly allows a positioning of the actuator in the upper part of the turbofan between the top beam of the thrust reverser and the pylon to free some space.

Abstract: An aircraft propulsion plant including an electric motor having a rotor and a stator mechanically linked to a base which can be mounted at the rear of an aircraft fuselage, a fan rotated by the rotor, a set of fixed blades located downstream of the fan, and a nacelle comprising an outer casing and a fan casing surrounding the fan and the set of fixed blades. The nacelle is mechanically linked to the base through the set of fixed blades. This configuration enables a cooling circuit to be formed for enabling the heat produced by the electric motor at the location of the stator to be evacuated towards the fixed blades and the nacelle where it is dissipated. Furthermore, this heat may be used for the de-icing of the nacelle lip.

Abstract: To control an engine shutdown in an aircraft, a control system includes a fuel supply shut-off member, a control member with a set of switches, a first switch on an electrical power supply link of the fuel supply shut-off member and second switches connected to avionics of the aircraft, the set of switches switching position on an engine shutdown command. An engine shutdown confirmation unit includes a third switch on the electrical power supply link, the third switch in open position by default. The engine shutdown confirmation unit includes electronic circuitry configured to switch the third switch over to closed position when a predefined quantity Q of switches of the control member switches position within a sliding window of predefined duration and, otherwise, keeps the third switch in open position. Thus, it is ensured that the engine shutdown is intentional.

Abstract: A device for monitoring clamping of an assembly including at least one part to be clamped, an internally threaded element and an externally threaded element engaged in an internal thread of the internally threaded element. The device includes a driver to rotate one of the elements including the internally threaded element and the externally threaded element to clamp the assembly and a first sensor to measure a screwing torque of the driver, a tool for holding fixed against rotation the other of the elements including the internally threaded element and the externally threaded element, a second sensor to measure a reaction torque of the holding tool, a mechanism for determining a third parameter chosen from a time elapsed from a given time and a screwing angle from a reference position, and a calculation system to determine pre-tension in the externally threaded element.

Abstract: A method and system for acquiring fuel characteristics on board an aircraft. The method for acquiring fuel characteristic on board an aircraft includes a least one tank and comprises a determination step determining a fuel circuit in one tank among the tank or tanks. The circuit includes at least one pump pumping the fuel from the tank into the circuit. A fuel properties measurement unit and a first valve are configured to open or close the circuit. A filling step includes filling the circuit with fuel. An acquisition step includes acquiring a value respectively for each of the fuel characteristics of the tank, and a transmission step includes transmitting, to a user device, a signal representative of the acquired values of the fuel characteristics.

Abstract: A method and system for synchronizing computers includes a bit computing module for computing of a bit by each computer, an exchange module, a bit signal pair determination module for determining a bit signal pair including the computed bit, a bit product pair determination module for determining a bit product pair indicating which bit equal to 1 of the bit signal pair of a computer can be combined with the bit of the bit signal pair determined for the other computer in the iteration n?1, a bit remainder pair determination module for determining a bit remainder pair indicating which bit equal to 1 of the bit signal pair of a computer in the iteration n is different from the bit of the bit signal pair of the other computer in the iteration n?1, a synchronized signal determination module for determining a synchronized signal based on the bit product pair and on the bit remainder pair.

Abstract: A method for detecting icing conditions for an aircraft including a measurement of the parameters of embedded systems, with the exception of probes dedicated to the detection of ice, a transformation of the measurements of the symptomatic parameters to obtain P-tuples of values of explanatory variables which explain icing conditions, a classification of the measurements by classifiers on the basis of the P-tuples of values thus obtained, the classifiers having been previously trained in a supervised manner, each classifier providing a prediction of membership in a class of icing conditions, the predictions of the various classifiers being consolidated to provide a consolidated prediction of icing conditions.

Abstract: A method and system for protecting an aircraft against an incoherent command instruction. The system has a generation unit generating a command instruction transmitted to an evaluation unit that evaluates whether or not the command instruction is incoherent and generates and transmits a validation order if the command instruction is coherent or an arbitration request if not, the arbitration request being transmitted by an arbitration unit, where applicable, to an operator who sends a confirmation response or a cancellation response. The arbitration unit generates and transmits a validation order to an execution unit in the event of receiving a confirmation response and a cancellation order in the event of receiving a cancellation response, the system allowing the execution unit to execute only the command instructions evaluated and confirmed as not being incoherent.

Abstract: Method and device for determining trajectory to optimal position of a follower aircraft with respect to vortices generated by a leader aircraft. The method includes controlling trajectory of a follower aircraft to an optimal position where the follower aircraft benefits from effects of at least one of the vortices of a leader aircraft. A first section control step controls flight of the follower aircraft using current measurements of flight parameters, from a safety position to a search position, along an approach section passing through an approach zone. A second section control step controls flight of the follower aircraft using current measurements of flight parameters, from the search position to a precision position, along a search section passing through a search zone, and a third section control step controls flight of the follower aircraft, from the precision position to the optimal position, along an optimization section passing through an optimization zone.

Abstract: Sound attenuation panel for aircraft having a combination of acoustic attenuation properties. The acoustic panel includes an acoustic structure having a cellular structure and a resistive skin and a backing skin, the acoustic panel also including at least one auxiliary acoustic device with cavities that is configured to produce additional acoustic absorption, the auxiliary acoustic device with cavities being attached to the acoustic structure and including adjacent chambers or cavities separated by shared walls, each of the chambers or cavities having perforations and being adapted to produce acoustic absorption. The combination of the acoustic structure and the auxiliary acoustic device with cavities enables combination of the acoustic absorption properties of these two types of element and an increased range of frequencies of the noise that can be attenuated by the acoustic panel without increasing its overall size.

Abstract: A coupling is disclosed providing fluidic continuity between first and second orifices of two portions of an air circuit which includes a flexible sleeve, a first frame connected in fluid-tight manner to a first end of the flexible sleeve and having a first opening, and a second frame, connected in fluid-tight manner to a second end of the flexible sleeve and having a second opening. The coupling is deformable so that the flexible sleeve may adapt to the variable spacing between two avionics racks and is able to compensate for a misalignment between the orifices of two portions of an air circuit.

Abstract: An actuating system for pivoting a wing tip section (13) about a fixed wing base section (11), and including a heating arrangement (33) positioned and adapted to be operable to heat at least one portion of an actuating arrangement (23) that pivots the wing tip section such that at least for ambient temperatures below a predetermined temperature the required work to be effected by the actuator (25) when moving the second coupling part (31) between the first position and the second position is lower than without heating the at least one portion.

Abstract: Method and system for merging measurements of flight parameters of an aircraft. The system is for merging measurements of flight parameters of an aircraft, linked to one another by at least one equation, and includes at least one acquisition module for acquiring at least one measurement of flight parameters, a scoring module for attributing a first validity score to the equations by checking whether the measurement or measurements of flight parameters are a solution or solutions of the equation or equations, a scoring module for attributing a second validity score to failure scenarios involving one or more acquisition modules from the first validity scores, a determination module for determining the validity of the measurements of flight parameters from the second validity scores, consolidation module for consolidating the measurements of flight parameters, a transmission module for transmitting the consolidated measurements of flight parameters to a user device.

Abstract: An assembly constituting an acoustically absorbent material and including a first panel, a second panel pierced with holes, an intermediate panel pierced with through-holes and arranged between the first panel and the second panel, a first structure between the first panel and the intermediate panel and including first cages, a second structure between the second panel and the intermediate panel and including second cages, and for each through-hole of the intermediate panel, a tube opening out at the two ends thereof, where one of the ends of the tube is fixed to the intermediate panel at the through-hole, and where the other end of the tube is accommodated inside a first cage. Such an assembly makes it possible to obtain broad-band attenuation and is easy to manufacture.