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.

Abstract: The invention relates to a method for determining the navigation speed of a carrier using a hybridization device (1) including a Kalman filter (3) developing a hybrid navigation speed (Vref) from inertial measurements calculated by a virtual platform (2) estimating a speed of the carrier (formula (I)) and frequency measurements outputted by a Doppler radar (4) having a multi-lobe antenna built therein, such that a Doppler frequency (F1, F2, F3, F4) is associated with each of the lobes, wherein said method includes the following steps: estimating, from the estimated speed (formula (I)), frequencies (F1, F2, F3, F4) corresponding to each of the Doppler frequencies (formula (II)) outputted by the radar; determining a group of observations where each observation represents an estimation deviation on the Doppler frequency associated with a lobe; calculating, by the Kalman filter (3), a speed correction (?V) to be applied to the estimated speed (formula (I)) on the basis of the group of observations.

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 characterised 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: The invention relates to a gyroscopic sensor comprising a sensitive element designed to vibrate; an electrode carrier capable of carrying electrodes for exciting the sensitive element and electrodes for detecting the vibration of the sensitive element; and support rods designed to support the electrode carrier, characterized in that the support rods have at least one bulged end.

Abstract: The invention relates to an orientation device comprising: a true north finder including a rate-gyroscope-type member, as well as sensors that can be used to measure the inclination of the device in relation to the horizontal, and associated calculation means for determining the orientation of the true north used on information provided by the rate gyroscope-type member and the sensors. According to the invention, the device also includes three feet that are used to support the device when it is placed on a support, at least one of said feet including a built-in sensor that changes state when the device is resting on a support by means of the feet, and means for automatically triggering the determination of the orientation of the north when the device is sufficiently horizontal and when the sensor indicates that it is placed on a support.

Abstract: The invention relates to an actuation system (100) for a propulsive unit including a nacelle, a turbojet engine, and an air circulation channel defined between the nacelle and the turbojet engine, the actuation system (100) including: a body and a connection device for attaching the body to the nacelle, the connection device enabling the body to move relative to the nacelle along two axes of rotation; a first member for moving a flap for controlling the airflow in the channel, the first member extending from the body and having a first point for attaching the first member to the flap; a second member for moving a thrust-reversing flap, the second member extending from the body and having a second point for attaching the second member to the flap, the body being arranged between the first and second attachment points; and a transmission device (40) having an input (42), a first output (44) connected to the first member (50), and a second output (43) connected to the second member (70), the transmission device

Abstract: An electronics module for use at high temperature (up to 225° C.) in onboard aviation equipment, the module having a thick layer hybrid circuit covered in a sealing coating of poly-p-xylylene.

Abstract: A method of managing execution of tasks by at least one processor unit of a computer system is provided, the processor unit operating in computation periods, and the method including the steps of associating time-related execution characteristics with each task, the time related execution characteristics including a flag indicating the possibility of determining, a priori, a theoretical time for the end of the task in a nominal execution mode, and a flag indicating the possibility of an extended execution mode whereby execution can continue beyond the theoretical end-of-execution time. When a task is being executed at the theoretical end-of-execution time, an execution continuation algorithm is launched in the presence of the flag indicating the possibility of extended mode, or an error processing algorithm is launched in the absence of such a flag.

Abstract: An electromechanical actuator for a movable flight control surface of an aircraft, the actuator comprising an electric motor having an outlet shaft with first and second directions of rotation, a movement transmission arranged to connect the outlet shaft of the motor to the movable flight control surface, and a control unit for controlling the motor. The transmission incorporates a pawl device arranged to oppose the transmission of movement in the first direction of rotation, and the control unit is connected to a pawl declutching member for declutching the pawl and enabling movement to be transmitted in the first direction of rotation.

Abstract: The electric motor consists of a rotor fitted with permanent magnets and comprises a stator the armature of which is made up of two parts: a stack of laminations forming round teeth and a solid tube-shaped field frame made of a material of the stainless steel kind enveloping the said stack of laminations. This armature constitutes a non-disengageable braking system that produces a damping effect in the face of possible movements of its rotor which are brought about and/or imposed by the members with which it collaborates. This motor can be used for driving a roto-linear actuator device with satellite rollers which is used as an actuator for maneuvering the control surfaces of an aircraft, for example an aileron.

Abstract: A method of detecting a fault of a switching electricity source having a control stage responsive to a setpoint signal to deliver a control signal that is modulated with a predetermined duty ratio (?) to a power stage that is to deliver electricity to a load. The method includes the steps of: determining at least one nominal value (?min, ?max) for the duty ratio for normal operation, and at least one fault threshold (?SC, ?OC) as a function of the nominal value; determining at least one instantaneous value (?) of the duty ratio of the signal issued by the control stage; and comparing the instantaneous value with the fault threshold. A detection circuit implementing the method is also provided.

Abstract: A device for generating a return force for a control stick that is movable from a neutral position along a travel path, includes a mechanical connection member connecting the stick to a resilient return member for returning the stick towards the neutral position. The mechanical connection member and the resilient return member produce, over a first portion of the travel path, a first strength of return force and, over a second portion of the travel path, a second strength of return force. A transmission part is mechanically connected to the stick so that any stick movement along the second portion corresponds to turning movement of the transmission part, and so that the return force to the stick is transmitted to the stick positioned in the second portion.

Abstract: A method of correcting the gain of a capacitive member having electrodes that are movable relative to each other including the steps of successively applying to one of the electrodes, reduced bias voltages having opposite signs and a common value below a threshold for which a remanent field generated by said reduced bias voltages can be measured, making corresponding measurements of the output signals from the capacitive member; taking an average, and correcting the gain of the capacitive member as a function of the measured output signal.

Abstract: A process for determination of navigation parameters of a carrier by a hybridisation device comprising a bank (3) of Kalman filters, each working out a hybrid navigation solution from inertial measurements calculated by a virtual platform (2) and raw measurements of signals emitted by a constellation of satellites supplied by a satellite-positioning system (GNSS), characterised in that it comprises the steps of: determination for each satellite of at least one probability ratio between a hypothetical breakdown of given type of the satellite and a hypothetical absence of breakdown of the satellite, declaration of a breakdown of given type on a satellite as a function of the probability ratio associated with this breakdown and of a threshold value, estimation of the impact of the breakdown declared on each hybrid navigation solution, and correction of hybrid navigation solutions as a function of the estimation of the impact of the breakdown declared.

Abstract: Method of angular measurement by means of a sensor comprising an axisymmetric resonator associated with means for setting the resonator into vibration and with means for detecting an orientation of the vibration with respect to a reference frame of the sensor, comprising the steps of applying a precession control so as to slave an orientation of the vibration to an angular setpoint value and of determining an angular measurement on the basis of the precession control. The method comprises a phase of modulating the angular setpoint value in such a way that the said setpoint value uniformly sweeps an angular span of ? radians and that a temporal derivative of the setpoint is deducted from the precession control prior to the determination of the angular measurement.

Abstract: An engine and pod assembly for an aircraft includes a pod receiving an engine having an air intake. A rotating nose cone extends on the nose cone, as well as a device for limiting the formation of ice. The device includes means for creating a circumferential heterogeneity of ice on the nose cone.

Abstract: A method of detecting a fault of a frequency sensor having a bias resistor and associated with a rotary member. The following steps are performed while the rotary member is stationary: injecting into the bias resistor of the sensor inverted alternating signals (S1, S2) comprising at least one first alternation (A1) and at least one second alternation (A2), the first alternation being of amplitude greater than the amplitude of the second alternation; and detecting a frequency of an output signal (S?) from the sensor. A measurement circuit implementing the method is also provided.

Abstract: A vibrating gyroscope has a base and a resonator. The resonator includes a body of generally cylindrical shape terminating in a face. The resonator is capable of vibrating according to a first vibration mode having antinodes distributed on n axes, and a second vibration mode having antinodes distributed on n other axes. The face of the resonator has two piezoelectric assemblies on each axis of the first and of the second vibration modes. Each piezoelectric assembly has at least one piezoelectric element capable of exciting the resonator in vibration and at least one piezoelectric element capable of detecting vibrations of the resonator at the same time.

Abstract: The invention relates to a system for actuating a plurality of actuators (15) that can move a mobile panel of an aircraft nacelle. Said system comprises at least two motors (16) that can drive the actuators (15), the two motors (16) being controlled and supplied by at least two separate control units (33, 35), and the actuators (15) being mechanically interconnected by a mechanical transmission (37). The invention also relates to a nacelle comprising such an actuating system.

Abstract: The invention concerns an opto-electronic device for observing and/or aiming at a scene comprising a target (C), comprising an observation module (1) comprising an image sensor (10) and a stabiliser (11) for a line of sight (100) towards the target (C); and a telemeter (2) comprising a multi-shot pulsed laser (20) for emitting a plurality of outward laser pulses (An) in the direction of the target (C) to be telemetered, and a detector (21) for a plurality of return laser echoes (Rn) reflected by the scene in order to generate an electrical signal for each return laser echo (Rn) in order to effect a measurement of the distance to the target (C), each return laser echo (Rn) corresponding to an outward laser pulse (An); characterised in that it also comprises a sensor (3) of angular movement of the device with respect to the stabilised line of sight (100) in order to determine an angular radius (?n) of each outward laser pulse (An) with respect to the stabilised line of sight (100); and a selector (4)