Abstract: A device for mechanically connecting a control surface to a fixed structural element of an aircraft, including a rotary actuator for driving an element that is securely connected to the control surface in rotation in relation to an element securely connected to the fixed structural element, around an articulation axis, as well as articulation elements for articulating this control surface around this axis. These articulation elements are able to support the control surface independently of the rotary actuator. This arrangement permits taking benefit from the advantageous properties of rotary actuators while allowing removal of the rotary actuator without having first to remove the control surface.

Abstract: The invention concerns a system for monitoring a flight control actuator of an aircraft, including: an actuator (1), sensors (3a-3d) in the actuator (1) to collect, during each flight of the aircraft, series of measurements of parameters relative to the said actuator, processing means (5) to calculate a set of damage indicators using, cumulatively, the series of measurements observed during each of the aircraft's successive flights, and a memory (7; 7a) to store the said set of damage indicators, where the said memory is integrated in the actuator.

Abstract: A device for mechanically connecting a control surface to a fixed structural element of an aircraft, including a rotary actuator for driving an element that is securely connected to the control surface in rotation in relation to an element securely connected to the fixed structural element, around an articulation axis, as well as articulation elements for articulating this control surface around this axis. These articulation elements are able to support the control surface independently of the rotary actuator. This arrangement permits taking benefit from the advantageous properties of rotary actuators while allowing removal of the rotary actuator without having first to remove the control surface.

Abstract: The invention relates to a flight control system for an aircraft comprising control surfaces and actuators associated with the control surfaces to control flight functions, including roll, yaw, pitching, and aerodynamic braking of the aircraft. The actuators associated with the control surfaces that control at least one of the flight control functions are electromechanical actuators. A part of the control surfaces associated with the electromechanical actuators is divided, where each of the divided control surfaces is comprised of at least two independent surfaces.

Abstract: According to this invention, artificial force gradient means (9a) of a throttle control lever (4) for a turbo-engine comprise means (17) for adjusting the intensity of the artificial force gradient.

Abstract: The invention concerns a system for monitoring a flight control actuator of an aircraft, including: an actuator (1), sensors (3a-3d) in the actuator (1) to collect, during each flight of the aircraft, series of measurements of parameters relative to the said actuator, processing means (5) to calculate a set of damage indicators using, cumulatively, the series of measurements observed during each of the aircraft's successive flights, and a memory (7; 7a) to store the said set of damage indicators, where the said memory is integrated in the actuator.

Abstract: The invention relates to a flight control system for an aircraft comprising control surfaces (111, 211, 331, 431, 541, 121-225), and actuators associated with said control surfaces to control flight functions of roll, yaw, pitching and aerodynamic braking of the aircraft. All of the actuators (111a1-211a2, 121a-225a) associated with the control surfaces controlling at least one of said flight functions are electromechanical actuators. A part of said control surfaces associated with the electromechanical actuators are divided control surfaces (111, 211, 331, 431, 541), each of said divided control surfaces being composed of at least two independent surfaces (113, 114, . . .

Abstract: According to this invention, artificial force gradient means (9a) of a throttle control lever (4) for a turbo-engine comprise means (17) for adjusting the intensity of the artificial force gradient.

Abstract: Some but not all engines of an aircraft are provided with thrust reversers. A safety device disables, at least from the position corresponding to idling, the action of the throttles corresponding to the engines devoid of thrust reversers when the thrust reversers are controlled to deployment.

Abstract: According to the invention, only certain engines (5, 6) of the aircraft are provided with thrust reversers (9, 10) and a safety device (33, 36, 37) is provided so as to disable, at least from the position corresponding to idling, the action of the throttles (13, 14) corresponding to the engines (7, 8) devoid of thrust reversers when said thrust reversers (9, 10) are controlled to deployment.

Abstract: A flying aid device for a fly-by-wire aircraft which has at least two mechanically independent control columns (M1, M2). The device (1) includes: a system (SO) for detecting multiple control corresponding to simultaneous operation of at least two of the control columns (M1, M2); and informing systems (S1, S2, S3, S4), each of which is associated with one of the control columns (M1, M2) and is intended to generate within the control column (M1, M2), when the detection system (SO) detects multiple control, a tactile sensation that informs a pilot of the aircraft who is operating the control column (M1, M2) of the multiple control.