Abstract: A flight control system for controlling the pitch of an aircraft having a vertical takeoff capability and an orientable lift direction may include a first device, to which a pitch command determined by a computing unit is applied, for actuating an element acting on the pitch of the aircraft. A second device of the flight control system receives an orientation order to actuate an element altering the orientation of the lift direction. Another device determines an orientation order for optimizing a flight parameter based on the pitch command determined by the computing unit. Yet another device subtracts from the pitch command the pitch contribution due to actuating the orientation element. The difference value acts as a pitch command to the first device.

Abstract: Flight control system for controlling the pitch of an aircraft with vertical takeoff and with an orientable lift direction.

Abstract: The present invention relates to a flight control device for an aircraft comprising a control (2) and a means for actuating a controlled member (RP, RQ) to which a command is applied. According to the invention, said device (1) additionally includes a sensor (E) for determining a second value that is representative of the control executed by the aircraft (He) with respect to the control axis, and second means (M2) which determine: as long as the second value is lower than or equal to a reference value, a first trim command that is proportional to the actuation of the control (2); and when the second value is higher than the reference value, in addition to a second trim command, a speed command that is proportional to the additional actuation over and above said second value.