초록 ▼

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

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).

대표청구항 ▼

1. A flight control system for yaw (Y) control of a rotorcraft having an anti-torque rotor, the control system comprising: at least one first drive channel making use of a rudder bar including a set of pedals operated by a human pilot and in communication with the anti-torque rotor via a remote mech

1. A flight control system for yaw (Y) control of a rotorcraft having an anti-torque rotor, the control system comprising: at least one first drive channel making use of a rudder bar including a set of pedals operated by a human pilot and in communication with the anti-torque rotor via a remote mechanical transmission mechanism suitable for varying the collective pitch of blades forming part of the anti-torque rotor;at least one second drive channel including calculation means with use thereof depending on a control button that can be actuated by a human pilot, the calculation means cause activation of at least one actuator for acting on the remote mechanical transmission mechanism, the actuator being at least one of a trim actuator and a series actuator for acting on the remote mechanical transmission mechanism in substitution for the first drive channel; andinhibit means for inhibiting the second drive channel, with use thereof depending on detector means for detecting operation of the rudder bar being moved by the human pilot;wherein the control system includes a third drive channel incorporating objective piloting means with use thereof depending on a movable control member operated by a human pilot, the movable control member issuing a control signal to an objective computer that generates a yaw command order relating to a state of progression to be achieved by the rotorcraft which order is sent to the calculation means of the second drive channel. 2. A control system according to claim 1, wherein use of the third drive channel depends on the inhibit means, action by the human pilot on the rudder bar deactivating use of the third drive channel. 3. A control system according to claim 1, wherein the control signal is an electrical signal issued continuously on the basis of a human pilot operating the movable control member without interruption, the control signal being proportional to the position of the movable control member relative to a predetermined rest station. 4. A control system according to claim 1, wherein the movable control member is operated by hand, being incorporated in a control stick. 5. A control system according to claim 4, wherein the movable control member is arranged as a button with unidirectional mobility for issuing the control signal. 6. A control system according to claim 4, wherein the control stick is a collective pitch varying control stick for use with a main rotor of the rotorcraft. 7. A control system according to claim 1, wherein the control signal relates to one of information about a rate of turn in yaw (Y) or information about a lateral load factor or information about yawing relative to the ground. 8. A control system according to claim 1, wherein the objective computer generates a command order on the basis of a comparison between the control signals relating to an objective flight control and an actual state of progression of the rotorcraft, and wherein the calculation means of the second drive channel generates activation commands for activating the actuator in response to the command order. 9. A control system according to claim 1, wherein the at least one actuator of the second drive channel is a “series” actuator, and wherein the objective computer includes means for recentering the “series” actuator by continuously controlling the 1 activation of a “trim” actuator independently of the human pilot operating the movable control member to generate any control signal. 10. A control system according to claim 1, wherein the objective computer comprises: a first calculation module in communication with the movable control member and serving to generate a setpoint signal on the basis of a control signal issued by the movable control member, the setpoint signal being weighted by observation information about a stage of flight of the rotorcraft; anda second calculation module that is in communication with the first module and that generates a command order derived from processing the difference between the setpoint signal and observation information about a change in the state of progression of the rotorcraft. 11. A control system according to claim 10, wherein the objective computer is in communication with a third calculation module that generates at least one activation command for activating the actuator on the basis of at least one command order generated by the second module. 12. A method of controlling the flight of a rotorcraft in yaw (Y) by using a control system according to claim 1, wherein the method comprises the following operations: sending to an objective computer a control signal that is delivered continuously by the human pilot operating the movable control member, the control signal relating to an objective flight command corresponding to a state of progression that the rotorcraft is to achieve;at least one sensor with which the rotorcraft is fitted detecting observation information about an actual state of progression of the rotorcraft;the objective computer deducing at least one command order by comparing the control signal and the observation information;on the basis of the command order, the calculation means of the second drive channel generating an activation command for activating at least one of the actuators; andthe calculation means of the second drive channel sending the activation command to the at least one of the actuators in order to operate the anti-torque rotor so as to cause the rotorcraft to pass from its actual state of progression to the state of progression that is to be achieved. 13. A flight control system for a rotorcraft with an anti-torque rotor, the flight control system comprising: a rudder bar with a set of pedals operable by a pilot;a mechanical transmission system configured to vary a collective pitch of blades of an anti-torque rotor in response to pilot operation of the pedals;an actuator configured to act on the mechanical transmission system;an autopilot control button;an autopilot system including a processor configured to control the actuator in the absence of pilot operation of the pedals, the autopilot system being activated in response to a pilot actuation of the autopilot control button;an inhibitor configured to, in response to pilot operation of the pedals, inhibit autopilot system control of the actuator;a control member; andan objective computer in communication with the processor and configured to, in response to pilot operation of the control member, generate a yaw command and command the autopilot system to control the actuator based on the yaw command. 14. The flight control system of claim 13, wherein the inhibitor is further configured to inhibit objective computer control of the actuator. 15. The flight control system of claim 13, further comprising a sensor, wherein the control member has a rest position, the sensor is configured to provide an electric control signal proportional to a position of the control member relative to the rest position. 16. The flight control system of claim 13, further comprising a flight control stick, wherein the control member is incorporated into the flight control stick. 17. The flight control system of claim 16, wherein the control member includes a button arranged for unidirectional travel. 18. The flight control system of claim 16, wherein the flight control stick includes a collective pitch varying control stick for use with a main rotor of the rotorcraft. 19. The flight control system of claim 13, wherein the actuator includes at least one of a trim actuator and a series actuator. 20. A rotorcraft comprising: an anti-torque rotor including a plurality of blades;a rudder bar with a set of pedals operable by a pilot;a mechanical transmission system configured to vary a collective pitch of the plurality of blades in response to pilot operation of the pedals;an actuator configured to act on the mechanical transmission system;an autopilot control button;an autopilot system including a processor configured to control the actuator in the absence of pilot operation of the pedals, the autopilot system being activated in response to a pilot actuation of the autopilot control button;an inhibitor configured to, in response to pilot operation of the pedals, inhibit autopilot system control of the actuator;a control member; andan objective computer in communication with the processor and configured to, in response to pilot operation of the control member, command the autopilot system to control the actuator to vary the collective pitch of the plurality of blades.