Patent ID: 6868315

Claim:
A flight control system for controlling at least the pitch of an aircraft with vertical takeoff, the lift direction of which can be oriented with respect to the aircraft structure, said flight control system comprising: at least a first control capable of being actuated by a pilot of the aircraft; at least a first actuator, to which a pitch command is applied, for actuating at least one controlled element capable of acting on the pitch of the aircraft; a computing unit for determining a first pitch command, depending on at least the actuation of said first control; at least a second control capable of being actuated by the pilot of the aircraft; at least a second actuator, to which an orientation order is applied, for actuating at least one orientable element making it possible to alter the orientation of the lift direction; and a first computer for determining and transmitting, to said second actuator, said orientation order dependent on at least the actuation of said second control, wherein said first computer automatically determines said orientation order making it possible to optimize at least one predetermined flight parameter, as a function of said first pitch command determined by said computing unit, and wherein said flight control system further comprises an auxiliary unit for subtracting from the first pitch command the pitch contribution due to actuating the at least one orientable element according to said orientation order, so as to obtain a second pitch command which is transmitted and applied to said first actuator for actuating the at least one controlled element.