Abstract: The invention relates to an electric circuit suitable for cutting off an electric power supply of an electric device, the circuit including an electrical device and a supply voltage source of the electrical device, also having as inputs at least two discrete electrical signals, the values of which condition the cutting off of the electric power supply of the device, the electric circuit being characterized in that same includes: at least two modules for cutting of the electric power supply connected between the voltage source and the electrical device, each module tar cutting off the electric power supply being controlled in accordance with the values of the discrete electrical signals; and at least two modules for comparing discrete electrical signals in parallel, in which at least one of the modules for cutting off the electric power supply is controlled by the outputs of the modules for comparing discrete signals.

Abstract: A method enabling an aerial drone not having a TCAS system to avoid an intruder aircraft, the method including the steps of acquiring the position of the intruder aircraft in order to determine the distance between the aerial drone and the intruder aircraft, measuring the angular speed of the intruder aircraft in a horizontal plane, and determining whether the intruder aircraft is fitted with a TCAS system, and, if so, receiving a resolution advisory transmitted by the TCAS of the intruder aircraft and following a previously-determined avoidance path. The invention also provides a drone fitted with a system implementing the method.

Abstract: An electromechanical actuator comprising a frame having mounted thereon a rotary motor and a gear train having an inlet shaft lying on the same axis as an outlet shaft of the motor and connected thereto, and an outlet ring coaxial with the outlet shaft of the motor and connected to a lever for operating a member that is to be driven. The gear train is carried by a casing mounted on the frame to pivot about the axis of the outlet shaft of the motor. An anti-blocking device is mounted on the frame and comprises a movable element that is movable between a blocking position for blocking the casing in rotation relative to the frame, and a release position for releasing the casing in rotation relative to the frame.

Abstract: The invention relates to a joystick (200) for controlling an aircraft, including a frame (201), a lever (202) mounted so as to be rotatably movable relative to the frame, and a mechanical linking assembly (203) for connecting the lever to the frame, the mechanical linking assembly (203) including: a first linking piece (213, 223) movably mounted relative to the frame (201) about a first rotation axis (X), a second linking piece (233, 243) movably mounted relative to the frame (201) about a second rotation axis (Y), the second rotation axis forming a non-zero angle with the first rotation axis, a third intermediate piece (255, 265) mounted so as to the rotatably movable relative to the first linking piece (213, 223) about a third rotation axis (Y?), a fourth intermediate piece (275, 285) mounted so as to be rotatably movable relative to the second linking piece (233, 243) about a fourth rotation axis (X?), the fourth rotation axis forming a non-zero angle with the third rotation axis, in which the linking piec

Abstract: A connection device for connecting an electrical member to a communications line comprising at least two conductors for carrying differential signals. The connection device includes at least one data exchange interface component connected to the line to send and/or receive data, and a connection for connecting the electrical member to the line.

Abstract: A gyroscopic system provides measurements on the basis of a vibrating gyroscope and provides a measurement signal. A periodic control signal is applied to it; in order to rotate the position of vibration, during a half period, according to a first speed profile, from a first up to a second position; and in order to rotate the position of vibration in an opposite direction during the other part of the period, according to a second speed profile, up to a third position. The measurements are based on corrected signals, each of said corrected signals, respectively for each of the vibrating gyroscopes, being obtained by; deducting the control signal from the measurement signal of the vibrating gyroscope; and taking account of errors identified on the basis of a comparison of the measurements provided by the gyroscopic system as a function of the position of vibration with reference measurements.

Abstract: The invention relates to a device (4) for actuating a control surface (2) of an aircraft, comprising: —a frame intended to be mounted fixed in relation to a structure of an aircraft, —a bell crank part (7) mobile in rotation in relation to the frame around an axis of rotation (X, X?) and adapted in order to be connected to a mechanical unit (1) for displacement of the control surface (2), —a slider (6) intended to be connected to a drive member (5), the slider (6) being mobile in translation in relation to the frame according to a direction of translation, parallel to the axis of rotation (X, X?) of the bell crank part (7), —first connecting means (61) between the slider (6) and the bell crank part (7) in order to convert a displacement in translation of the slider (6) generated by the drive member (5) into a displacement in rotation of the bell crank part (7), in order to actuate the mechanical unit (1) for displacement of the control surface (2), an input part (53, 16) able to be driven in rotation by the m

Abstract: Method of angular measurement by a resonator associated with a vibration setting device and with a vibration detector, which are linked to a processing circuit through which there travel control signals and measurement signals, the method comprising the steps of digitizing the measurement signals and of deducing an angular measurement from the measurement signals. The method comprises the steps of performing a spectral analysis of the digitized measurement signals so as to detect harmonic distortions therein and correcting at least some of the signals travelling through the processing circuit so as to attenuate the non-linearities.

Abstract: A module converting voltage between a high-voltage electrical network and at least one energy storage element an aircraft, the conversion module configured to reversibly convert between a DC voltage of the high-voltage electrical network and a DC voltage of the energy storage element, the DC voltage of the energy storage element floating relative to the DC voltage of the high-voltage electrical network and centered relative to the mass of the aircraft, the module including an input module including two filters each capable of receiving a DC voltage, a first arm and a second arm including switches, and a mechanism controlling the switches, operating per cycle of a switching period and capable of controlling at least one first switch and at least one second switch identically but offset by a half-period, whereby the first switch is open when the second switch is closed and vice versa.

Abstract: The invention concerns an electric circuit designed to control a power supply of a piece of electrical equipment, the electric circuit comprising a piece of electrical equipment and a source of supply voltage, and further having, as inputs, at least two discrete electrical signals of which the values condition the cutting off of the power supply to the piece of equipment, the circuit being characterised in that it further comprises:—a module for the redundant comparison of the discrete electric signals, comprising two branches for comparing said signals, parallel to one other, each branch being designed to supply, at the output, a control signal representative of each of the comparisons of said discrete electrical signals, and—a first module for cutting off the power supply to the piece of electrical equipment comprising two switches in series, each one being controlled respectively by one of the two control signals.

Abstract: A method for demodulating at least one received frame is provided, where the frame includes of a succession of bits coded according to a Manchester code. The method includes the steps of: generating an interruption at least at each appearance of a rising and/or falling edge of the frame of coded bits; determining the time between each interruption from at least one first counter; reinitialising the demodulation of the frame as soon as one of the determined times is less than a first predetermined value or greater than a second predetermined value, the first and second predetermined values being dependent on the duration of a bit coded according to the code; and demodulating, for each determined time, if the determined time is greater than the first predetermined value and is less than the second predetermined value, at least one binary value of the frame from the determined time.

Abstract: The invention relates to an on-board assembly for producing and storing electricity, including at least one hydrogenerator having an output line connected to at least one electrical battery having predetermined electrical load parameters. The hydrogenerator includes a load-bearing structure onto which a generator and an impeller, secured to a shaft for driving a rotor of the generator, are mounted. Said assembly is characterized in that the generator is an excitation generator, and the hydrogenerator includes a rectifier circuit, connecting the generator to the output line, and at least one circuit for exciting the generator. The excitation circuit is connected to an excitation current regulator controlled by a control unit set up so that the generator provides a load current consistent with the electrical load parameters on the basis of a resisting torque of the generator, said torque being predetermined so as to limit drag of the impeller.

Abstract: A lightning protection component, with at least one main input capable of transmitting a lightning signal, at least one main output designed to be connected to a piece of equipment (T) to be protected from the lightning signal, a branched output designed to be connected to a dissipation circuit (M), a direct line connecting the main input to the main output, a bypass circuit that is mounted between the direct line and the branched output, and that is provided with at least one bypass switch having an open state in which the branched output is isolated from the direct line and a closed state in which the lightning signal is conducted from the direct line to the branched output.

Abstract: The method of aligning an inertial unit having an axially symmetrical vibrating sensor that generates vibration comprises the step of establishing the vibration in a position for which the sensor presents variation in drift error that is the smallest relative to variation in drift error for other positions of the vibration.

Abstract: Configurable generic electrical facility comprising processing means for implementing at least one configured function, the processing means comprising a processing unit, predefined functional blocks being implemented in the processing unit, the processing unit comprising a memory module designed to store configuration data, characterized in that the processing unit comprises routing means designed to connect the blocks and to organize data exchanges between the blocks according to interconnection data included in the configuration data stored in the memory module 5.

Abstract: A pressure sensor made of semiconductor material, the sensor comprising a box defining a housing under a secondary vacuum, at least one resonator received in the housing and suspended by flexible beams from at least one elastically deformable diaphragm closing the housing that also contains means for exciting the resonator in order to set the resonator into vibration and detector means for detecting a vibration frequency of the resonator. The detector means comprise at least a first suspended piezoresistive strain gauge having one end secured to one of the beams and one end secured to the diaphragm. The resonator and the first strain gauge are arranged to form zones of doping that are substantially identical in kind and in concentration.

Abstract: A method of operating actuators simultaneously for moving at least two aircraft movable aerodynamic surfaces, the method comprising the steps of: controlling the actuators to move the aerodynamic surfaces towards a predetermined position; during the movement, detecting a slowest actuator; and adapting the control of the actuators to match the actions of the slowest actuator. A drive device for aerodynamic surfaces and an aircraft including such a device.

Abstract: The invention relates to an actuating device comprising: —a first element (7), —a second element (8) able to move translationally with respect to the first element (7), and —a locking device (6) comprising a catch (18, 20) able to move between a deployed position and a retracted position, the catch (18-20) being positioned with respect to the first element (7) in such a way that when the catch (18-20) is in a deployed position, the catch (18-20) allows the second element (8) to move with respect to the first element (7) in a first range of movement (A) and prevents the second element (8) from moving with respect to the first element (7) in a second range of movement (B), and when the catch (18-20) is in the retracted position, the catch (18-20) allows the second element to move with respect to the first element (7) in the second range of movement (B).

Abstract: An AC/DC converter comprising an input rectifier circuit connected in series with a primary winding (5) of an isolating transformer (6) and to a chopper switch (T1) driven by a control circuit (10) using pulse width modulation on the basis of a signal representative of a primary current, the isolating transformer having a first secondary winding (7) that is wound in the same direction as the primary winding and that is connected to an output line (8) of the converter via a diode (D4) and a filter coil (L1), and a second secondary winding (9) that is wound in the opposite direction to the primary winding and that is connected directly to the output line via a diode (D2), the output line being connected to an output capacitor (Cout).

Abstract: Gyroscopic measurements are provided, by a system comprising a vibrating gyroscope, in the form of an output signal. The vibrating gyroscope provides an original measurement signal. A periodic control signal (CP) is applied to it over a time period, which signal is suitable: for rotating the geometric position of vibration in a first direction, during a part of the time period; and for rotating the geometric position of vibration in a second direction opposite to the first direction, during the other part of the time period; said control signal having a zero mean over said time period and exhibiting portions of signal at high frequency relative to the output signal; said output signal being based on a corrected signal emanating from the original measurement signal; in which the corrected signal is based on an identification of errors made during the signal portions at high frequency.