Abstract: A control system for an actuator including a straight slot direct current motor comprises a position sensor for measuring the angular position (?) of the motor and a current sensor for measuring the current strength (Im) in the motor, but not having a sensor for measuring the angular rotation speed of the motor.

Abstract: A monitoring and control device for an aircraft actuator includes a control module, delivering control signals for the actuator and position signals for the actuator determined according to control messages received from a piloting management system of the aircraft, and at least one first position sensor supplying information concerning the position of the actuator, and a monitoring module, delivering position signals for the actuator and receiving the control signals received from the piloting management system of the aircraft, and information relating to the position of the actuator supplied by at least one second position sensor. The control and monitoring modules are capable of assessing the consistency of the signals processed therein and of controlling accordingly a power supply and disabling module of the actuator.

Abstract: A control system for an actuator including a straight slot direct current motor comprises a position sensor for measuring the angular position (?) of the motor and a current sensor for measuring the current strength (Im) in the motor, but not having a sensor for measuring the angular rotation speed of the motor.

Abstract: A monitoring and control device for an aircraft actuator includes a control module, delivering control signals for the actuator and position signals for the actuator determined according to control messages received from a piloting management system of the aircraft, and at least one first position sensor supplying information concerning the position of the actuator, and a monitoring module, delivering position signals for the actuator and receiving the control signals received from the piloting management system of the aircraft, and information relating to the position of the actuator supplied by at least one second position sensor. The control and monitoring modules are capable of assessing the consistency of the signals processed therein and of controlling accordingly a power supply and disabling module of the actuator.

Abstract: An automatic piloting device utilizing a measurement of ground speed deduced from the measurements of acceleration originating from an AHRS attitude and heading platform which it readjusts by ground speed information provided by a T readjustment device: satellite-based positioning receiver or a Doppler radar exhibiting periods of unavailability. This automatic piloting device includes a preprocessing part with readjustment blocks based on estimator filters of the complementary type of second order with two branches one of the first order, the other of the second order which are momentarily transformed into first-order complementary filters, by action on their branch gains, with each return of availability of the readjustment device.

Abstract: The invention pertains to an automatic piloting device utilizing a measurement of ground speed deduced from the measurements of acceleration originating from an AHRS attitude and heading platform which it readjusts by means of ground speed information provided by a T readjustment device: satellite-based positioning receiver or a Doppler radar exhibiting periods of unavailability. This automatic piloting device comprises a preprocessing part with readjustment blocks based on estimator filters of the complementary type of second order with two branches one of the first order the other of the second order which are momentarily transformed into first-order complementary filters, by action on their branch gains, with each return of availability of the readjustment device.

Abstract: The present invention relates to the redundant architectures of processing lines interposed between primary flight equipment doubled or tripled as a safety measure and one or more flight conduct systems. It relates more particularly to the addition, at the head of the processing lines, of anti-noise filters intended to avoid untimely disconnections of an automatic control of a flight conduct system that are not justified by a suspected failure. These anti-noise filters are digital filters operating at the sampling rate of the output signals of the primary flight equipment and not at the lower rate of flight conduct systems.

Abstract: A method and device are provided for guiding an aerodyne on the runway, picularly during the taxiing phase preceding take off, the device including an inertial unit adapted for delivering signals representative of the North speed, of the East speed, of the azimuth and of the ground speed of the aerodyne. From these signals, a computer elaborates a parameter defining the axis of the runway, during an apprenticeship step during which the aerodyne, guided on site by the pilot, taxies along the axis of the runway, and stores this parameter at the end of the step. The computer then delivers to the means piloting the aerodyne a synthetic runway aberration signal between the axis of the runway thus stored and the position of the aerodyne delivered by the inertial unit.

Abstract: A process and system for the rapid detection of a wind gradient or change r an aircraft. Such a system provides for, on the one hand, the rapid detection of important or significant wind gradients or changes which can occur during the final phase of approach preceding the landing of the aircraft and, on the other hand, to inform the pilot or the automatic flight control system of the existence of this wind gradient sufficiently early to permit necessary corrective action to be taken.