Abstract: A system monitors the health of a helicopter, and includes a device for determining a change of state of the engine and is configured to collect data measured by engine and external conditions sensors during a stable flight phase and to process the measured data.

Abstract: A turbine for a turbine engine extending along an axis includes an annular casing and at least one turbine stage having a nozzle and a rotor impeller wheel surrounded by a sealing ring with an abradable element. The impeller wheel and the sealing ring are located downstream of the nozzle, and the sealing ring has an upstream end held on the casing by locking means. The turbine includes elastic sealing means in contact with the locking means as well as with the nozzle or the casing so as to press the locking means against the sealing ring. The locking means includes a radially outer portion with a C-shaped cross-section and a radial portion extending radially inwards from the outer portion. The sealing means include two elastic seals bearing on the radial portion, respectively, on either side of the radial portion.

Abstract: A method for determining an efficiency fault of at least one module of a turboshaft engine of an aircraft. The method comprising a step of determining an estimated real mapping, a step of determining real indicators from the estimated real mapping, a step of determining a plurality of simulated mappings from a simulation of a theoretical model of the turboshaft engine for different efficiency configurations, a step of determining simulated indicators for each simulated mapping, a step of training a mathematical model by coupling the simulated indicators with efficiency configurations, and a step of applying said mathematical model to the real indicators so as to deduce therefrom a real efficiency configuration.

Abstract: A device for monitoring a state of a propulsion engine includes an acquisition module that acquires data of flights of the propulsion engine, comprising, for each flight, values of input variables, environment variables, and output variables of the propulsion engine during the flight, a learning module that computes, by learning from the data of each flight, an individual flight model for the flight, a using module that computes, for each flight, estimates of the values of the output variables, by applying the individual flight model to reference values of the input variables and the environment variables, and an error associated with the estimates of the values of the output variables that is obtained by applying the individual flight model to the reference values of the input variables and the environment variables. The reference values belong to a set of reference data, which are identical for the individual flight models.

Abstract: A method for evaluating the state of an aircraft engine for a given flight, each flight of the aircraft being associated with one time-domain series, includes, each time maintenance of the aircraft is performed, creating a dataset including the time-domain series associated with each flight carried out between the maintenance and the preceding maintenance; creating a set of datasets including each created dataset and dividing it into a training set and a validating set; conjointly training an embedding function and a classifier, selecting a reference time-domain series from a time-domain series of the validating set; and computing a distance between the embedment associated with the time-domain series of the given flight and the embedment of the reference time-domain series, with a view to computing an indicator of engine state.

Abstract: A turbine for a turbine engine extending along an axis includes an annular casing and at least one turbine stage having a nozzle and a rotor impeller wheel surrounded by a sealing ring with an abradable element. The impeller wheel and the sealing ring are located downstream of the nozzle, and the sealing ring has an upstream end held on the casing by locking means. The turbine includes elastic sealing means in contact with the locking means as well as with the nozzle or the casing so as to press the locking means against the sealing ring. The locking means includes a radially outer portion with a C-shaped cross-section and a radial portion extending radially inwards from the outer portion. The sealing means include two elastic seals bearing on the radial portion, respectively on either side of the radial portion.

Abstract: A device for monitoring a state of a propulsion engine includes an acquisition module that acquires data of flights of the propulsion engine, comprising, for each flight, values of input variables, environment variables, and output variables of the propulsion engine during the flight, a learning module that computes, by learning from the data of each flight, an individual flight model for the flight, a using module that computes, for each flight, estimates of the values of the output variables, by applying the individual flight model to reference values of the input variables and the environment variables, and an error associated with the estimates of the values of the output variables that is obtained by applying the individual flight model to the reference values of the input variables and the environment variables. The reference values belong to a set of reference data, which are identical for the individual flight models.

Abstract: A system for monitoring an aircraft engine, including an acquisition module for acquiring current measurements of physical quantities, referred to as input and output physical sizes, relative to the aircraft engine, a module for simulating the physical behavior of the aircraft engine, in order to simulate output physical quantities as a function of the current measurements of input physical sizes, a processor for calculating physical margins, referred to as actual physical margins, between the simulated values of output physical quantities and the corresponding current measurements of output physical quantities, a learning module for predicting margins, the margins being predicted using current measurements of input physical quantities and wherein the processor is configured to calculate surveillance residuals giving an indication of the state of the aircraft engine.

Abstract: A system monitors the health of a helicopter, and includes a device for determining a change of state of the engine and is configured to collect data measured by engine and external conditions sensors during a stable flight phase and to process the measured data.

Abstract: A method for determining a droop response profile of a rotating electrical machine supplying electricity to an electrical grid having a network frequency varying on either side of a nominal frequency, in which a measured value of the rotation speed of the rotating machine is retrieved, and the droop response parameters dependent on the measured speed value are defined. The droop response profile is a graph centered on the coordinates of an origin point between 99% and 101% of the measured speed and defined by at least two points of coordinates in the case of underspeed and/or by at least two points of coordinates in the case of overspeed, each of the points having for its abscissa a speed value as a percentage of the measured speed, and for the ordinates, a filtered speed value as a percentage of the measured speed modulated by at least one of the droop response parameters.

Abstract: The invention relates to an actuation device (10) comprising: detection means configured to supply a position of an object interfering with at least one electromagnetic field; a means for determining a speed of motion of the object according to the position of the object supplied by the detection means; and actuation means configured to actuate an action if: the detection means supply a position of the object, and the speed of the object is lower than a predefined speed value.

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: 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: The control device comprises at least one emitter-receiver pair, a display and a controller. The emitter-receiver pair comprises a radiation emitter and a receiver for receiving radiation emitted by the emitter and reflected by a moving body located at a distance from the pair. The receiver is positioned within the emitter's emission field and provides an electrical signal representative of the radiation received from the emitter. At least one symbol identifying an action, opposite an intersection of the emitter's emission cone and the receiver's reception cone, is displayed. The emitter and receiver are outside the display area of each symbol. The controller provides action control signal according to the electrical signal provided by the receiver. Each emitter-receiver pair is associated with at least one symbol and at least one action control signal when the moving body is in front of the symbol that identifies the action.

Abstract: A method of applying a protective coating by spraying onto annular protuberances of a component includes at least one first element and an annular portion bearing the protuberances extending axially from a side wall of the first element, wherein a first protuberance is arranged axially closest to the first element and bears a face opposite to the first element, wherein the method has the following stages: arranging reflection means axially between said side wall of the first element and the first annular protuberance, and spraying, via the spraying means, a spray of a protective material towards the reflection means such that the spray of protection impacts the face, opposite to the first element, of the first protuberance.

Abstract: A method for determining a droop response profile of a rotating electrical machine supplying electricity to an electrical grid having a network frequency varying on either side of a nominal frequency, in which a measured value of the rotation speed of the rotating machine is retrieved, and the droop response parameters dependent on the measured speed value are defined. The droop response profile is a graph centered on the coordinates of an origin point between 99% and 101% of the measured speed and defined by at least two points of coordinates in the case of underspeed and/or by at least two points of coordinates in the case of overspeed, each of the points having for its abscissa a speed value as a percentage of the measured speed, and for the ordinates, a filtered speed value as a percentage of the measured speed modulated by at least one of the droop response parameters.

Abstract: The control device comprises at least one emitter-receiver pair, a display and a controller. The emitter-receiver pair comprises a radiation emitter and a receiver for receiving radiation emitted by the emitter and reflected by a moving body located at a distance from the pair. The receiver is positioned within the emitter's emission field and provides an electrical signal representative of the radiation received from the emitter. At least one symbol identifying an action, opposite an intersection of the emitter's emission cone and the receiver's reception cone, is displayed. The emitter and receiver are outside the display area of each symbol. The controller provides action control signal according to the electrical signal provided by the receiver. Each emitter-receiver pair is associated with at least one symbol and at least one action control signal when the moving body is in front of the symbol that identifies the action.

Abstract: The invention describes a new class of crystalline silica material having two levels of porosity and structural order. At the first level, building units are nanoslabs of uniform size having zeolite framework. At the second structural level, nanoslabs are assembled, e.g. linked through their corners, edges or faces following patterns imposed by interaction with cationic surfactant or triblock copolymer molecules. After evacuation of these molecules, microporosity is obtained inside the nanoslabs, and a precise mesoporosity between the nanoslabs depending on the tiling pattern of the zeolite nanoslabs, as evidenced by X-ray diffraction. These materials are useful for the fixation of biologically active species, such as poorly soluble drugs.