Abstract: The method comprises the following successive steps: — depositing sintering material (26) onto one of an electronic component (28) and a substrate (30); — heating the material (26) so as to bring a temperature of the material to a preliminary exothermic peak, which precedes an exothermic sintering peak, without the temperature of the material reaching a maximum of the preliminary exothermic peak; — fastening the other of the component (28) and the substrate (30) to the material (26) so that the material is interposed between the component and the substrate; and— pressing the material (26) while hot so as to cause it to creep.

Abstract: A non-return device for coaxial rotation transmission includes coaxial input and output shafts, a frame for guiding the rotation of the shafts. A locking element is urged in radial translation through a channel of the output shaft between a radial locking position, in which the locking element projects from the channel so as to prevent a rotation of the output shaft by abutting against the frame, and a radial unlocking position, in which the locking element is retracted so as to allow axial rotation of the output shaft. The input shaft includes means for radially switching the locking element between the locking and unlocking positions thereof.

Abstract: This inertial navigation unit comprises a navigation data acquisition unit (1) and a first navigation stage (2) capable of calculating hybrid navigation values by combining navigation data.

Abstract: This bistable switch (24) is intended to be fitted in an aircraft and comprises a frame (26) and a control means (34, 94) which is intended to be operated by a user, the control means (34, 94) being movable relative to the frame (26) between a first control position and a second control position. This switch (24) comprises a leaf spring (52) which is mechanically connected to the frame (26) and to the control means (34, 94), the leaf spring (52) being arranged in a buckling state and being configured to switch between the two control positions in each of its two stable buckling positions, respectively.

Abstract: The present invention relates to a bidirectional data communication method for a bidirectional data communication system (100), in particular an embedded bidirectional data communication system (100), comprising: at least one first communicating device (200a) configured to implement a single-pair Ethernet protocol and one second communicating device (200b) configured to implement a single-pair Ethernet protocol and comprising a second packet management module (220b) connected to a first physical link management module (231b) and to a second physical link managment module.

Abstract: A piloting device arranged to be integrated in a pre-existing aircraft that includes original systems comprising both a flight control system and an autopilot system is distinct from and autonomous relative to the original systems and includes a positioning unit and a control unit. The positioning unit is arranged to produce positioning data for the pre-existing aircraft. The control unit is arranged to perform a geofencing function from the positioning data produced by the positioning unit and to produce an alternative piloting setpoint for the pre-existing aircraft. The alternative piloting setpoint is adapted to supplement both a manual piloting setpoint produced by a pilot of the pre-existing aircraft via the flight control system and also an autopilot setpoint produced by the autopilot system.

Abstract: A telescope including a fastener plate, a primary mirror carried by a front face of the plate, and a secondary mirror held facing the primary mirror by a support, wherein the support includes a primary sleeve mounted around the primary mirror, a secondary sleeve mounted around the secondary mirror, and arms connecting the secondary sleeve to the primary sleeve, and in that the arms are curved towards the primary mirror.

Abstract: Angular sensor with vibrating resonator includes a supporting structure, a first mass and a second mass which are concentric, and mechanical springs arranged symmetrically in pairs, the pairs themselves being arranged symmetrically with respect to one another. Each spring comprises a first elastic leaf and a second elastic leaf which are connected to one another by one end, the first elastic leaf of one of the springs of each pair being parallel to the second elastic leaf of the other of the springs of the same pair. The four elastic leaves of at least one pair comprise two adjacent pairs of leaves making an angle of approximately 45° between them. The sensor is not provided with electrostatic springs.

Abstract: Rudder pedal and brake inceptor devices are described that utilize a straight-line mechanism and rotary joints to achieve straight line motion in a compact volume. The devices can include four or more bar linkages that translate forward motion of a pedal into a rotary motion of a common shaft, such that forward motion of one pedal causes the other pedal to retract while allowing for yaw motion control of the aircraft.

Abstract: A method for assisting with the navigation of a fleet of vehicles including a main vehicle and a secondary vehicle that is mobile in relation to the main vehicle, the method including receiving relative movement data, acquired by one or more sensors, between the main vehicle and the secondary vehicle, estimating a navigation status of the fleet of vehicles by an invariant Kalman filter using the received data as observations, the navigation status including first variables representing a first rigid transformation linking a location mark associated with the main vehicle to a reference point, and second variables representing a second rigid transformation linking a location mark associated with the main vehicle to a location mark associated with the secondary vehicle, the invariant Kalman filter using, as an internal composition law, a law including a term-by term composition of the first rigid transformation and the second rigid transformation.

Abstract: The invention relates to an electric machine comprising a rotor and a stator. The rotor (40, 4) comprises a plurality of permanent magnets (4), the stator comprises a plurality of coils suitable for being powered by an electric current and two Hall effect sensors (6) on supports (60). The sensors are configured to detect a change in gradient of the normal component of a magnetic field generated by the permanent magnets (4). The stator comprises a part (7) comprising —a first zone (7a), —a second zone (7b), and a third zone (7c) extending from the first zone (7a) up to the second zone (7b). The maximum radial thickness of the third zone (7c) is less than the minimum radial thickness of the first zone and the second zone.

Abstract: A system for firing a projectile mounted on a carrier, the decision assistance system comprising: a first simulator for simulating a navigation system of the carrier and configured to produce a precision of a solution for navigation of the carrier; a second simulator for simulating a navigation system of the projectile and configured to be initialized with the precision of the solution for navigation of the carrier and produce a precision of a solution for navigation of the projectile; and a selector configured to select or not the projectile as projectile to be fired as a function of the precision of a solution for navigation of the projectile.

Abstract: A method and a device for monitoring a region (R) in which a carrier (100) is located, which device comprises a display unit displaying a polar plot (10) having a center symbolizing the current position of the carrier (100) and in which there is placed a first moving-body symbol (1, 2, 3) representing the current position of the moving body (101, 102, 103); the polar plot (10) being surrounded by an annular band (20) of width (l) representing a predetermined monitoring duration and containing second moving-body symbols (1?, 2?, 3?) representative of successive angle readings of the path of said moving body (101, 102, 103).

Abstract: An accelerometer sensor includes a casing, a pendulum fixed to the casing, a movable electrode carried by the pendulum and connected to a detection circuit, a first electrode and a second electrode rigidly attached to the casing to form, with the moving electrode, two capacitors of variable capacitance depending on a distance between the electrodes. The accelerometer sensor further includes a control unit that carries out detection operations to measure the variable capacitances of the capacitors. The control unit also performs a control operation of the movable electrode depending on the capacitances measured by applying a logic signal for controlling a switch for selective connection of the fixed electrodes to an excitation circuit delivering a control signal to the fixed electrodes in order to keep the pendulum in a predetermined position.

Abstract: A method for controlling an engine, a device for controlling an engine and an aircraft, the method comprising the steps of determining a first intensity Kp, representing a stiffness, according to a physical stiffness Kss of the mechanical connection and a stiffness setpoint Kpspec to be rendered on the control column, a second intensity Kv, representing a damping, according to a physical damping fss between the control column and the engine and a damping setpoint Kvspec to be rendered on the control column, and a third intensity Ka, representing an inertia, according to a physical inertia Jss of the control column and an inertia setpoint Kaspec to be rendered on the control column.

Abstract: Process for protecting a part comprising an aluminum-based alloy having a copper content greater than or equal to 0.5% by mass, the process comprising depositing a non-conductive protective layer over the entire part, laser pickling by means of a laser beam of an area of the non-conductive protective layer so as to form an unprotected area, chemical conversion, with trivalent chromium, of the unprotected area so as to form a conductive protective layer, and drying of the part.

Abstract: Process for protecting a part comprising an aluminum-based alloy, the process comprising depositing a primer paint layer by anaphoresis over the entire part, polymerizing the primer paint layer in order to form a non-conductive polymerized primer paint layer, laser pickling, by means of a laser beam, an area of the non-conductive polymerized primer paint layer in order to form an unpainted area, trivalent chromium chemical conversion of the unpainted area in order to form a conductive protective layer and drying the part, depositing a finishing paint layer on at least a portion of the non-conductive polymerized primer paint layer, and polymerizing the finishing paint layer.

Abstract: An antenna in a system is provided and includes a first device and at least one second mobile device, where the first device communicates with the second device(s). In an acquisition mode, for each antenna of an antenna system, a first item of communication quality information is obtained, and the antenna the first item of information of which is the highest is selected. In a pursuit mode, if the selected antenna is sectoral, a second item of communication quality information is obtained, and the antenna the second item of information of which is the highest is selected. For each antenna, a third item of communication quality is obtained if the selected antenna is the omnidirectional antenna, and from the third items of information, the antenna the third item of information of which is the highest is selected.

Abstract: A method for measuring the hardware and operational state of a dual-circuit solenoid valve including first and second coaxial coils each associated with a circuit is disclosed. The method includes the steps of injecting a sinusoidal current into the first coil; measuring the voltage induced across the terminals of the second coil; and plotting at least one curve of a first magnitude proportional to the measured induced voltage as a function of a second magnitude proportional to the injected sinusoidal current.

Abstract: The invention relates to a force application device for a control stick of an aircraft, said control stick comprising a control lever that is connected to at least one motor comprising a drive shaft that can be rotated about an axis, the force application device comprising: a first pin connected to the shaft, a housing, an electromagnet, a movable actuator comprising a magnetic material, a coupling device comprising an input gear connected to the housing and an output gear comprising a second pin, and means for clamping the first pin and the second pin which comprise a first tooth and a second tooth, said device having an operating configuration in which the electromagnet is active and the output gear is positioned at a distance from the input gear, and a blocking configuration in which the electromagnet is inactive and the gears are meshed.