Abstract: An actuator for at least one flight control surface of an aircraft. The actuator has at least two actuator members for actuating the flight control surface between two extreme positions and a motor connected to the actuator members by at least one rotary motion transmission line. Each actuator member includes a drive pinion and the actuator is arranged so that the transmission line has an angular amplitude of less than one revolution during movement of the flight control surface between its two positions. The motion transmission line is arranged to allow only one angular position between the drive pinions and the actuator member.

Abstract: An actuator for at least one flight control surface of an aircraft. The actuator has at least two actuator members for actuating the flight control surface between two extreme positions and a motor connected to the actuator members by at least one rotary motion transmission line. Each actuator member includes a drive pinion and the actuator is arranged so that the transmission line has an angular amplitude of less than one revolution during movement of the flight control surface between its two positions. The motion transmission line is arranged to allow only one angular position between the drive pinions and the actuator member.

Abstract: The invention relates to an actuator (4) for controlling a horizontal stabilizer (3) of an aircraft, including: a primary channel including a screw (6) and a primary nut (7), the primary nut (7) being suitable for engaging with the screw (6), such that a rotation of the screw (6) relative to the primary nut (7) about a rotation axis (X) causes the primary nut (7) to translate relative to the screw (6) along the axis (X), such as to move the horizontal stabilizer (3); a secondary channel including a secondary part (25, 28), and a housing (23, 26), the secondary part (25, 28) being mounted in the housing (23, 26) with play between the secondary part and the housing, in which the secondary channel also includes a play take-up device (27), configured to, in the event of a breakdown of the primary channel causing the secondary part (25, 28) to move relative to the housing, eliminate the play between the secondary part (25, 28) and the housing (23, 26) such as to keep the secondary part (25, 28) in contact with the

Abstract: The invention relates to an actuator (4) for controlling a horizontal stabiliser (3) of an aircraft, including: a primary channel including a screw (6) and a primary nut (7), the primary nut (7) being suitable for engaging with the screw (6), such that a rotation of the screw (6) relative to the primary nut (7) about a rotation axis (X) causes the primary nut (7) to translate relative to the screw (6) along the axis (X), such as to move the horizontal stabiliser (3); a secondary channel including a secondary part (25, 28), and a housing (23, 26), the secondary part (25, 28) being mounted in the housing (23, 26) with play between the secondary part and the housing, in which the secondary channel also includes a play take-up device (27), configured to, in the event of a breakdown of the primary channel causing the secondary part (25, 28) to move relative to the housing, eliminate the play between the secondary part (25, 28) and the housing (23, 26) such as to keep the secondary part (25, 28) in contact with the

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: 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 invention relates to a method of feeding energy to actuators associated with the undercarriages forming the landing gear of an aircraft, the aircraft comprising: a main power supply that operates independently of rotation of wheels carried by the landing gear; and a local power supply comprising one or more local generators, each driven by rotation of a wheel carried by an undercarriage; the method of the invention comprising the following steps: in a nominal mode of operation, powering said actuators by the local power supply; and in an additional mode of operation, when the delivery of energy by the local power supply is not sufficient, providing additional energy or all of the energy required by said actuators by means of the main power supply.

Abstract: The invention relates to a method of feeding energy to actuators associated with the undercarriages forming the landing gear of an aircraft, the aircraft comprising: a main power supply that operates independently of rotation of wheels carried by the landing gear; and a local power supply comprising one or more local generators, each driven by rotation of a wheel carried by an undercarriage; the method of the invention comprising the following steps: in a nominal mode of operation, powering said actuators by the local power supply; and in an additional mode of operation, when the delivery of energy by the local power supply is not sufficient, providing additional energy or all of the energy required by said actuators by means of the main power supply.