Abstract: An electronic device for diagnosing the condition of a system of actuators of an aircraft turbine engine, the device being configured to be coupled to an electrical wiring harness of a turbine engine connecting a computer of a turbine engine to a system of actuators of the turbine engine, the device including a power supply block to power the device, a connection block configured to enable the connection of the device to the electrical wiring harness of the turbine engine to be diagnosed, a communication block configured to send information to a user and to receive instructions from the user, and a control block including a test signal transmission module and modules for measuring the signals received by the device in response to the test signals over a work cycle of the system of actuators of the turbine engine.

Abstract: A cooling system for cooling an aircraft turbojet engine includes a first heat-exchanger for exchanging heat between a heat-transfer fluid and a lubricant of the turbojet engine, a second heat-exchanger for exchanging heat between the heat-transfer fluid and air, and a circulation duct for circulating heat-transfer fluid in a closed circuit. The cooling system further includes at least one regulating device for regulating the heat drawn from the lubricant, controlled by a control module of the regulating device that is configured to receive information according to the various flight phases.

Abstract: Described herein are methods and compositions comprising nicotinamide riboside and alpha-ketoglutarate for treating frailty, for maintaining health, and for re-growing hair.

Abstract: A method for commanding a plurality of virtual personal assistants, the commanding method being carried out by a control system, the control system being adapted to communicate with each virtual personal assistant, the control system in particular being a control system embedded in a vehicle. The method includes the steps of: receiving a request from a user, the request including a message; selecting a virtual personal assistant as a function of the message; obtaining a selected virtual personal assistant; and sending a command to the selected virtual personal assistant.

Abstract: Storage compartment for a vehicle comprising: a receptacle having an interior volume; a movable partition member that can be moved in a sliding direction and partitions said interior volume, and; a locking device for locking the partition member in the sliding direction, comprising a first locking member provided on the receptacle and suitable for engaging with a second locking member provided on the partition member; the partition member being movable in an unlocking direction perpendicular to the sliding direction between a locked position in which the first and second locking members engage and a sliding position in which the first and second locking members are disengaged from each other, and the compartment comprising an elastic member biasing the partition member towards the locked position.

Abstract: The present disclosure provides an electric de-icing/anti-icing device for a turbojet engine or turbo-prop nacelle element to be protected from icing. The device includes: a heating assembly including first and second heating stages positioned in the nacelle element; an electricity supply circuit delivering a primary voltage to the first heating stage of the heating assembly. In particular, the electricity supply circuit includes an electricity source, and a de-icing/anti-icing circuit which is connected to the heating assembly and supplied voltage by the electricity source. Furthermore, the de-icing/anti-icing device includes components to supply a complementary voltage to the second heating stage of the heating assembly.

Abstract: The present invention relates to a method for commanding and controlling at least one resistive heating element (1) belonging to an aircraft turbojet engine nacelle deicing set, characterized in that it involves the steps aimed at: obtaining, from a central control unit (6) of the aircraft, parameters representative of the exterior flight conditions; determining a thermal model corresponding to the flight conditions obtained; as a function of the thermal model, delivering the appropriate corresponding electrical power (4) to the resistive heating element.

Abstract: Storage compartment for a vehicle comprising: a receptacle having an interior volume; a movable partition member that can be moved in a sliding direction and partitions said interior volume, and; a locking device for locking the partition member in the sliding direction, comprising a first locking member provided on the receptacle and suitable for engaging with a second locking member provided on the partition member; the partition member being movable in an unlocking direction perpendicular to the sliding direction between a locked position in which the first and second locking members engage and a sliding position in which the first and second locking members are disengaged from each other, and the compartment comprising an elastic member biasing the partition member towards the locked position.

Abstract: The invention relates to a de-icing device for an element of a nacelle of a turbojet engine, including at least one heating resistant mat connected to at least one electrical power source (3) and thus defining an assembly (1) of resistant mats, characterized in that the assembly of resistant mats includes one or more subassemblies of resistant mats, each subassembly in turn including one or more resistant mats of the assembly, and each subassembly of resistive mats having a different ohmic value.

Abstract: An electrical heating assembly is provided for a defrosting device of an air-intake lip of a turbojet engine nacelle. The electrical heating assembly includes a current-conductive portion and a resistive portion, and the resistive portion includes strips spaced apart one another. Each strip is connected to the current-conductive portion so as to form at least one recess in the resistive portion.

Abstract: A lip assembly of a turbojet engine nacelle is equipped with at least one electric de-icing system. The lip assembly includes at least one electric heating member, electrically powered through at least one power conductor. Each power-supply conductor is associated with a neutral conductor or “ground” arranged in a regrouped manner adjacent to a corresponding power-supply conductor.

Abstract: The invention relates to a method for controlling a plurality of actuators (9a, 9b, 9c) for a movable thrust reverser cowl (1), characterized remarkable in that the position deviation between adjacent actuators is measured in real time, and in that the speed profile of the actuator or actuators in question is adjusted by a position deviation exceeding a predetermined threshold.

Abstract: A nacelle for a turbojet engine includes an air inlet forward section, a median section surrounding a fan of the turbojet engine, an aft section equipped with a thrust reverser system, a power control unit able to convert a high voltage electric supply into an electric supply towards an electromechanical actuator, and a drive unit for the power control unit which is distinct and separate from the latter and has a control input and a drive output to be connected to the power control unit. The thrust reverser system includes a mobile cowl which, under action of an electromechanical actuator, is able to move from a closed position to an open position in which the mobile cowl opens a passage in the nacelle.

Abstract: A nacelle for receiving an aircraft engine, the nacelle having a tubular stationary cover and at least one movable portion connected to the stationary cover via movement means for moving the movable portion between a position close to the stationary cover and a position spaced apart therefrom. The movement means have asynchronous motors, each having a stator with windings connected in parallel to a power supply circuit and a rotor having windings, each connected to a resistive load in parallel with a winding of the rotor of each of the other motors.

Abstract: A lip assembly of a turbojet engine nacelle is equipped with at least one electric de-icing system. The lip assembly includes at least one electric heating member, electrically powered through at least one power conductor. Each power-supply conductor is associated with a neutral conductor or “ground” arranged in a regrouped manner adjacent to a corresponding power-supply conductor.

Abstract: The present invention relates to an electric power supply circuit (1) for a turbojet engine nacelle including at least one electric generator (2) mechanically connected to the shaft of a turbojet engine, said generator being capable of directly supplying electric power to a first electric power device other than a simple monitoring or supervising unit, characterized in that said generator is capable of directly supplying electric power to at least one second electric power device other than a monitoring or supervising unit, as well as to a nacelle including such an electric circuit.

Abstract: The invention relates to a device (9) for controlling the maintenance actuators (7a, 7b) of the cowlings of a turbojet engine nacelle of an aircraft, that comprises a first stage (12) to be connected to an electric power network (10) of the aircraft, at least one second power stage (13a, 13b) including converters of a first DC voltage from the first stage (12) into a second DC voltage for powering at least one maintenance actuator (7a, 7b) connected downstream from the device (9), a control means (14) for the first and second stages (12, 13a, 13b), and a means (15) for establishing a communication between the control means (14) and at least one control housing (16a, 16b) so that a user can control the operation of the actuators, the control means being arranged so as to carry out switching operations between a first operation mode in which the second stage(s) (13a, 13b) are powered, and a second standby mode in which the second stage(s) (13a, 13b) are not powered by the first stage (12).

Abstract: The invention relates to a method and a device for controlling the power supply of at least one aircraft maintenance actuator (7) from an electrical power supply network (10) of the aircraft comprising means (14) for controlling the electrical power supply of at least one maintenance actuator, and means (15) for establishing communication between the control means and at least one control unit (16) allowing a user to control the operation of at least one actuator. The control means are designed to compare the state of at least one control unit with at least one reference state (SBR) and/or an abnormal state (SBE1, SBE2, SBE3) for switching-on purposes, and to prohibit the activation of the actuator if the state of the control unit is different from a reference state (SBR) or corresponds.

Abstract: The present invention relates to an electric power supply circuit (1) for a turbojet engine nacelle including at least one electric generator (2) mechanically connected to the shaft of a turbojet engine, said generator being capable of directly supplying electric power to a first electric power device other than a simple monitoring or supervising unit, characterized in that said generator is capable of directly supplying electric power to at least one second electric power device other than a monitoring or supervising unit, as well as to a nacelle including such an electric circuit.

Abstract: A nacelle for receiving an aircraft engine, the nacelle having a tubular stationary cover and at least one movable portion connected to the stationary cover via movement means for moving the movable portion between a position close to the stationary cover and a position spaced apart therefrom. The movement means have asynchronous motors, each having a stator with windings connected in parallel to a power supply circuit and a rotor having windings, each connected to a resistive load in parallel with a winding of the rotor of each of the other motors.