Abstract: A method of harmonizing a first inertial measurement unit and a second inertial measurement unit with each other includes the steps of: causing a control unit to compare the vectors measured by the inertial measurement units in order to determine a specific force difference and a rotation difference while taking account of the lever arms between the two measurement units; and causing the control unit to determine a harmonization value from the specific force difference and the rotation difference while taking account of the lever arms between the two measurement units. Navigation apparatus performs the method.

Abstract: A method for estimating a Remaining Useful Life of a subject equipment, with a preliminary phase including the following steps: acquire test observations (step 10) and produce test time series (Sx) of at least one signature; partition the test time series to obtain severity classes corresponding to the ageing phases of the test equipment devices (step 14); carry out an initial learning of a diagnosis model on the test equipment devices (step 45); perform a second learning of a signature prediction model (step 51). There is also an operational phase including the following steps: acquire observations when in operation on the subject equipment and produce an extrapolated time series using the prediction model; classify the extrapolated time series using the diagnosis model and derive the remaining useful life of the subject equipment.

Abstract: A method of assembling together a first part and at least one second part that are made of materials compatible with bonding by molecular adhesion includes a step of pressing a first surface of the first part against a second surface of the second part so as to create molecular bonds at an interface between the parts, and a step of consolidating the interface bonding as created in this way by heat treatment. The consolidation includes a step of emitting a power laser beam towards an impact point forming a portion of the outline of the interface, and a step of moving the impact point along the outline of the interface.

Abstract: The invention relates to an aircraft control column, the control column comprising a first shaft and a control lever configured to rotate the first shaft about a first axis through a first angular range [?1; ?3] via a mechanical joint having a primary reduction ratio, the control column comprising a braking device configured to brake the first shaft via a first transmission device having a secondary reduction ratio, the secondary reduction ratio being maximum for an angular position, the secondary reduction ratio increasing over the range [?1; ?4] and then decreasing over the range [?4; ?3] so as to obtain an overall reduction ratio that has a limited amplitude of variation over the first angular range [?1; ?3].

Abstract: A method for secure pairing between a sensor and a concentrator using a mobile terminal includes generating and emitting a confirmation code by the concentrator; converting by the sensor of the confirmation code into a sequence of light signals executed by at least one light-emitting diode; converting by the mobile terminal of the sequence of light signals into a sequence code; sending the sequence code to the concentrator; comparing, by the concentrator, the sequence code and the generated confirmation code: if the sequence code does not match the generated confirmation code, generating a warning; if the sequence code matches the generated confirmation code, pairing and exchanging information between the sensor and the concentrator.

Abstract: The system for controlling the speed of opening a sliding door for an aircraft including a mechanical braking device for the door including a transmission shaft and a centrifugal absorber including a resistance shaft connected to the transmission shaft, and linking means that are designed to be connected to the sliding door and to cooperate with the transmission shaft so that when the sliding door moves in a predetermined direction, the linking means drive the transmission shaft and the centrifugal absorber applies a resistance torque to the transmission shaft in order to control the speed of movement of the door. The system includes a speed reducer connecting the resistance shaft to the transmission shaft so that the speed of rotation of the resistance shaft is greater than that of the transmission shaft when the sliding door moves in the predetermined direction.

Abstract: A system for updating data for computer devices included in an aircraft, the computer devices being, when the data is updated, liable to affect or not the safety of an operator performing maintenance, the system is included in the aircraft and includes a data loading device, a communication device, a data router and a module for detecting at least one maintenance operation on the aircraft. The system includes: means, included in the communication device, for receiving a command for updating a computer device; means, included in the communication device, for controlling the data loading device and the data router in order to transfer the updating data to the computer device; and means, controlled by the module for detecting at least one maintenance operation on the aircraft, for blocking the updating if at least one signal indicating that a maintenance operation is being performed on the aircraft is received.

Abstract: This parachute comprising a canopy having a leading edge and a trailing edge opposite the leading edge, suspension lines each having a first end attached to the leading edge and a second end that is designed to bear a load, and a slider having through-elements for the suspension lines to pass through, said elements being connected to one another by attachment means, each of said through-elements being passed through by one of the suspension lines and being free to move in translation relative thereto, the slider being designed to slide along the suspension lines that pass through the through-elements in the direction from the first ends of said suspension lines towards their second ends under the effect of gravity and the force generated by the suspension lines spreading apart when the parachute starts a descent, tightening and spreading apart the suspension lines as the canopy inflates.

Abstract: The system for controlling the speed of movement of a sliding door for an aircraft comprises a means for electromagnetically braking the door including a transmission shaft and electromagnetic resistive means. The resistive means are autonomous and include a control law relating a first damping value to a first speed threshold of the speed of movement of the door, a second damping value to a second speed threshold of the speed of movement of the door, the resistive means applying on the transmission shaft the resistive torque equal to a first torque proportional to the first damping value when the speed of movement is higher than the first speed threshold, and applying the resistive torque equal to the sum of the first torque and of a second torque proportional to the second damping value when the speed of movement is higher than the second speed threshold.

Abstract: A system for controlling the activation/deactivation of an electromagnetic shielding screen of a porthole or a protective window of an optoelectronic equipment, which includes, a radiofrequency electromagnetic sensor, with a bandwidth adapted to a cut-off band of said shielding screen corresponding to a range of electromagnetic fields to be blocked, connected to a detector-rectifier with a sensitivity higher than a minimum value of the power of an electromagnetic field to be blocked by means of said shielding screen and a device for activating/deactivating said electromagnetic shielding screen, said detector-rectifier being configured, in the presence of the electromagnetic field with a power exceeding said minimum value, to activate said device for activating/deactivating the electromagnetic shielding screen by capturing the electromagnetic energy supplied by said electromagnetic fields with a power exceeding said minimum value.

Abstract: The invention relates to a method for estimating the direction of arrival of an electromagnetic wave at an antenna array (2), comprising the steps of: —estimating (202) a covariance matrix of signals acquired by the antenna array (2); —calculating (204) a normalised eigenvector of the covariance matrix; —correlating (205) the normalised eigenvector with a first reference table and a second reference table so as to produce a first correlation spectrum and a second correlation spectrum comprising correlation indices associated, respectively, with different directions of arrival; —constructing (312) a third reference table by linear combination of the first reference table and the second reference table with a polarisation component of the electromagnetic wave in the first direction and the second direction, respectively; —correlating (314) the normalised eigenvector with the third reference table so as to produce a third correlation spectrum comprising correlation indices associated with different directions of

Abstract: An autonomous impact detection device includes at least one impact detector; at least one wireless transmission device configured to transmit the information collected by the impact detector; at least one energy storage device configured to supply the impact detector and the wireless transmission device with energy; at least one Seebeck module configured to supply the storage device with energy when a temperature gradient is applied thereto; the wireless transmission device being configured to supply the storage device with energy when the temperature gradient to which the Seebeck module is exposed is not sufficient.

Abstract: The electrical insulating element for a stator comprising a stack of magnetic sheets having at least one first stator tooth and comprising at least one first stator coil wound around the first stator tooth, the first stator tooth having a first end face located at one end of the stack of magnetic sheets, the insulating element comprises an electrically insulating foil having a face coated with adhesive. The insulating element is configured to be inserted between the first face of the first stator tooth and the stator coil, the face coated with adhesive being adhered to the first face.

Abstract: The invention relates to a device (2) for transferring heat from a thermally conductive plate (30) capable of capturing the heat from a zone placed on a first side (32) of the plate, the device comprising at least one fin (35) placed on a second side (34) of the plate (30) opposite the first side (32) and having a duct (36) extending in a longitudinal direction (L) between a first end (38) connected to the plate and a second end (40) opposite the first end and which opens out, the duct (36) being connected to at least one Venturi-effect neck (42) bringing cooling air into the duct, the neck (42) being formed in the vicinity of the first end of the duct and the plate (30).

Abstract: An acquisition and analysis device to be integrated in a pre-existing aircraft that includes original systems comprising pilot controls and also an autopilot system includes acquisition means arranged to acquire parameters produced by the original systems, and analysis means arranged on the basis of the parameters, to evaluate whether the pre-existing aircraft is normal or abnormal, and to evaluate the current stage of flight of the pre-existing aircraft, on the basis of the state of the pre-existing aircraft and of the current stage of flight of the pre-existing aircraft, to define a piloting setpoint selected from piloting setpoints comprising at least a manual piloting setpoint produced by a pilot actuating pilot controls, an autopilot setpoint produced by the autopilot system, and an alternative piloting setpoint, and to cause the selected piloting setpoint to be transmitted to the original systems of the pre-existing aircraft.

Abstract: The invention relates to an optronic sight (2) for a motorised vehicle such as an aerial, marine or land vehicle, comprising a sighting module (4) able to be moved about a first axis (8a) and a second axis (10) not parallel to the first axis (8a), means (17a, 17b) for moving the sighting module about the first (8a) and second (10) axes, means (14) for continuously measuring an angular datum of said module (4) about the first and second axes characterised in that it comprises a feedback control loop comprising: means for acquiring the fundamental frequency of vibratory disturbances generated by the operation of at least one device of the sight, and an adaptive corrector (26) configured to receive as input: said fundamental frequency, a discrepancy between an angular setpoint value (yck) and said angular datum outputting a movement setpoint value to the movement means (17a, 17b).

Abstract: The invention relates to a device for measuring the oxidation of an element comprising a carbon-carbon composite, including a means for measuring the diamagnetism of the element and a means for converting the diamagnetism measurement into an oxidation measurement.

Abstract: The disclosure relates to a housing comprising at least one composite wall comprising woven or braided carbon fibers covered with a thermoplastic or thermosetting resin, an electronic card carrying electronic components, and a heat transfer device having at least one portion facing an electronic component to be cooled of the electronic card, said heat transfer device being inserted inside the composite wall, the heat transfer device comprising at least one cooling conduit containing a cooling fluid.

Abstract: The invention relates to a method for locating a target by means of a detecting device comprising a photodetector comprising N×M quadrants positioned with respect to a sighting axis of the detecting device, the photodetector being configured to detect optical signals from the target to be detected, said method being implemented in a processing unit of said device and comprising the following steps, the target scattering an optical signal: —acquiring the signals detected by each quadrant, which correspond to the signals scattered by the target toward the quadrants; —processing the acquired signals to determine an elevation angle error and an azimuth angle error of the direction of the target with respect to the sighting axis of the device; —processing the acquired signals with a view to deducing therefrom indicators of the distribution of the signals detected by the quadrants; —processing the determined elevation angle error and azimuth angle error with a view to deducing therefrom indicators of the theoretica

Abstract: A method for navigating a carrier using a Kalman filter estimating a navigation state of a carrier, comprising: obtaining, from a signal transmitted by the satellite and subsequently received by the carrier, a delta range measured between the carrier and a satellite and another measured kinematic datum which is associated with the satellite, generating, from position data for the carrier and the satellite in the navigation state, an estimated delta range between the carrier and the satellite, calculating, using the delta ranges, a delta range innovation associated with the satellite, carrying out a test on the delta range innovation, the test result indicating whether or not the signal was a multi-path signal, using, by means of the filter, the kinematic datum as an observation to update the navigation state provided that the test result indicates that the signal was not a multi-path signal.