Rotorcraft anti-torque systems and methods therefor
A method of providing an anti-torque force in a rotorcraft with an anti-torque system comprised of a primary ducted tail rotor system mechanically connected to an engine, and a secondary ducted tail rotor system electrically connected to an electric power supply. The method includes receiving an indication of a change in the operating condition of the anti-torque system based upon a change in a rotorcraft condition input, a feedback input associated with a primary ducted tail rotor system and/or a secondary ducted tail rotor system, and/or a pilot input; responsive to the indication of the change, determining, by a control system, an anti-torque control input including at least a secondary output command for controlling the secondary ducted tail rotor system; and transmitting the secondary output command to the secondary ducted tail rotor system to energize at least one ducted tail rotor assembly therein to provide the second anti-torque force.
1. A method of providing an anti-torque force in a rotorcraft; the rotorcraft having an anti-torque system comprised of a primary ducted tail rotor system mechanically connected to an engine and configured to provide a first anti-torque force on the body of the rotorcraft, and a secondary ducted tail rotor system electrically connected to an electric power supply and configured to provide a second anti-torque force on the body of the rotorcraft; the method comprising:
receiving an indication of a change in the operating condition of the anti-torque system based upon a change in at least one of the following: a rotorcraft condition input from a rotorcraft condition sensor, a feedback input from at least one feedback sensor associated with a primary ducted tail rotor system and/or a secondary ducted tail rotor system, and a pilot input from at least one pilot control;
responsive to the indication of the change in the operating condition of the anti-torque system, determining, by a control system, an anti-torque control input including at least a secondary output command for controlling the secondary ducted tail rotor system; and
transmitting the secondary output command to the secondary ducted tail rotor system to energize at least one ducted tail rotor assembly therein to provide the second anti-torque force
wherein the change in the operating condition comprises determining that the rotorcraft is in a noise-sensitive area,
the method further comprising:
the step of determining an anti-torque control input achieved by implementing an acoustic signature loop to generate:
a primary output command for controlling the primary tail rotor system and the secondary output command
to achieve a desired acoustic signature of the anti-torque system based upon a predetermined acoustic signature, and
wherein the determining of a noise-sensitive area and a current anti-torque system acoustic signature are each based upon at least one of the following:
the rotorcraft condition input,
a feedback input, and/or
the pilot input,
which is then used to determine an appropriate action of the at least one ducted tail rotor assembly to achieve the desired acoustic signature;
wherein the secondary output command is determined and generated in accordance with the determined appropriate action of the at least one ducted tail rotor assembly.
2. The method according to claim 1 , replaced with wherein the step of determining an anti-torque control input including at least a secondary output command is determined by at least another one of the following: an auxiliary loop, a primary malfunction loop, and a secondary malfunction loop.
3. The method according to claim 1 , wherein the control system is a fly-by-wire flight system.
4. The method according to claim 1 , wherein the at least one pilot control comprises a pedal assembly including a pedal and a pedal sensor operably associated with the pedal and configured to detect displacement of the pedal; wherein the indication of a change in the operating condition comprises sensing displacement of the pedal by the pedal sensor.
5. The method according to claim 4 , wherein the pedal is configured to be positioned to a first position to indicate a change in the operating condition of the primary ducted tail rotor system and a second position to indicate a change in the operating condition in the secondary ducted tail rotor system.
6. The method according to claim 4 , the method further comprising:
the step of determining an anti-torque control input including at least the secondary output command is achieved by implementing an auxiliary loop to generate the secondary output command.
7. The method according to claim 6 , wherein the auxiliary loop determines a current anti-torque system performance based on rotorcraft condition input from the rotorcraft condition sensors and determines a desired second anti-torque force based upon the displacement of the pedal, which are then used to determine an appropriate action of the at least one ducted tail rotor assembly to achieve the desired amount of second anti-torque force;
wherein the secondary output command is determined and generated in accordance with the determined appropriate action of the at least one ducted tail rotor assembly.
8. The method according to claim 1 , wherein the change in the operating condition comprises sensing a malfunction, a pending malfunction, or loss of the primary ducted tail rotor system, the method further comprising:
the step of determining an anti-torque control input including at least the secondary output command is achieved by implementing a primary malfunction loop to generate the secondary output command.
9. The method according to claim 8 , wherein the primary malfunction loop determines a primary ducted tail rotor system performance and determines a desired second anti-torque force based upon the rotorcraft condition input, a feedback input, and/or the pilot input, which is then used to determine an appropriate action of the at least one ducted tail rotor assembly to achieve the desired second anti-torque force;
wherein the secondary output command is determined and generated in accordance with the determined appropriate action of the at least one ducted tail rotor assembly.
10. The method according to claim 1 , wherein the secondary ducted tail rotor system comprises a first ducted tail rotor assembly and a second ducted tail rotor assembly, wherein the change in operating condition is comprised of sensing a malfunction, a pending malfunction, or loss of the first or second ducted tail rotor assembly, the method further comprising:
the step of determining an anti-torque control input including at least the secondary output command is achieved by implementing a secondary malfunction loop to generate the secondary output command for controlling a functioning first or second ducted tail rotor assembly.
11. The method according to claim 10 , wherein the secondary malfunction loop determines a current secondary ducted tail rotor system performance and determines a desired second anti-torque force based upon the rotorcraft condition input, a feedback input, and/or the pilot input, which is then used to determine an appropriate action of the functioning first or second ducted tail rotor assembly to achieve the desired amount of second anti-torque force;
wherein the secondary output command is determined and generated in accordance with the determined appropriate action of the functioning first or second ducted tail rotor assembly.
12. The method according to claim 10 , further comprising:
augmenting the second anti-torque force provided by the functioning first or second ducted tail rotor assembly to align the second anti-torque force provided by the functioning first or second ducted tail rotor assembly with the desired anti-torque system performance.
13. The method according to claim 1 , wherein the step of determine an appropriate action further comprises determine an appropriate action of the primary ducted tail rotor system to achieve the desired acoustic signature and generate a primary output command in accordance with the determined appropriate action of the primary ducted tail rotor system.
14. The method according to claim 13 , wherein when entering a noise-sensitive area, the secondary output command increases a rpm and/or a collective of the blades in at least one ducted tail rotor assembly in the secondary ducted tail rotor system and the primary output command decreases an rpm and/or a collective of the blades in the primary ducted tail rotor system.
15. The method according to claim 1 , wherein the acoustic signature loop further comprises sending an acoustic signature output including at least one of a current acoustic signature display and a desired acoustic signature display to an output interface.
16. The method according to claim 1 , wherein the desired acoustic signature is selected from a database having a plurality of predetermined acoustic signatures.
17. The method according to claim 1 , wherein the acoustic signature loop is automatically implemented when the rotorcraft is in or near a noise-sensitive area.
18. The method according to claim 1 , wherein the determining of a noise-sensitive area and the desired acoustic signature is based on the pilot input including a primary input and a secondary input, which is then directly transmitted to the control system for determining at least a secondary output command and a primary output command.