Abstract: A method of controlling a path of a rotorcraft. The method comprises a step of generating a first path setpoint and a step of automatically generating a first autopilot command from the first path setpoint. The method comprises a step of generating a first pilot setpoint during which a movement of a control member is transformed into a first pilot setpoint, the first pilot setpoint and the first flight parameter being homogenous in that they are expressed in the same measurement unit. The method includes a step of generating a first human pilot command from the first pilot setpoint followed by a step of generating a path command by combining the first autopilot command and the human pilot command.

Abstract: A method of controlling a path of a rotorcraft. The method comprises a step of generating a first path setpoint and a step of automatically generating a first autopilot command from the first path setpoint. The method comprises a step of generating a first pilot setpoint during which a movement of a control member is transformed into a first pilot setpoint, the first pilot setpoint and the first flight parameter being homogenous in that they are expressed in the same measurement unit. The method includes a step of generating a first human pilot command from the first pilot setpoint followed by a step of generating a path command by combining the first autopilot command and the human pilot command.

Abstract: A method of controlling a path of a rotorcraft. The method comprises a step of generating a first path setpoint and a step of automatically generating a first autopilot command from the first path setpoint. The method comprises a step of generating a first pilot setpoint during which a movement of a control member is transformed into a first pilot setpoint, the first pilot setpoint and the first flight parameter being homogenous in that they are expressed in the same measurement unit. The method includes a step of generating a first human pilot command from the first pilot setpoint followed by a step of generating a path command by combining the first autopilot command and the human pilot command.

Abstract: A method of controlling a path of a rotorcraft. The method comprises a step of generating a first path setpoint and a step of automatically generating a first autopilot command from the first path setpoint. The method comprises a step of generating a first pilot setpoint during which a movement of a control member is transformed into a first pilot setpoint, the first pilot setpoint and the first flight parameter being homogenous in that they are expressed in the same measurement unit. The method includes a step of generating a first human pilot command from the first pilot setpoint followed by a step of generating a path command by combining the first autopilot command and the human pilot command.

Abstract: A system and a method for controlling a rotorcraft (1) in yaw (Y). The control system comprises a plurality of drive channels that operate an anti-torque rotor (4) of the rotorcraft (1). A first drive channel makes use of a rudder bar (13) including a set of pedals operated by the human pilot of the rotorcraft in order to control the anti-torque rotor (4). A second drive channel includes an autopilot. A third drive channel includes objective-type flight control means comprising a movable control member (12) that is operated by the human pilot and that continuously issues control signals (11) relating to a state of progression that the rotorcraft (1) is to achieve. Use of the second drive channel and of the third drive channel depends on inhibit means (19) for inhibiting operation thereof, which means are activatable by detector means (37) for detecting operation of the rudder bar (13).

Abstract: A flight control device for an aircraft, in particular for a helicopter, includes, in addition to a control member and an actuator of a controlled member, a determination unit for determining a control command which corresponds to a translational rate control command, dependent on the deflection of the control member, while the translational rate of the aircraft is less than a reference value and which corresponds otherwise to a translational acceleration or angular rate control command, dependent on an extra deflection of the control member.

Abstract: The flight control device (1) comprises, in addition to a control member (2) and to a means of actuation of a controlled member (RP, RQ), a means of determination (MD) for determining a control command which corresponds to a translational rate control command, dependent on the deflection of the control member (2), while the translational rate of the aircraft (He) is less than a reference value and which corresponds otherwise to a translational acceleration or angular rate control command, dependent on an extra deflection of the control member (2).

Abstract: Flight control system for a rotary-wing aircraft, particularly for a helicopter. The flight control system comprises at least one flight control (LCo, MCy, Pal), first commands being representative of the position of a flight control (LCo, MCy, Pal), an assisted flight control system (CDVE) generating assistance values representing second commands, first unit (CDVE) for determining the control commands from the sum of the first and second commands, and a limitation system (SL) which limits the assistance values to first limited values. This limitation system (SL) additionally comprises unit for calculating the difference between the assistance values and the first limited values, and unit for calculating the sum of the first limited values and of difference and for transmitting it as second commands.

Abstract: Flight control system for a rotary-wing aircraft, particularly for a helicopter.