Tail rotor balancing systems for use on rotorcraft

1. An electrically distributed yaw control system for a helicopter having a tailboom, the electrically distributed yaw control system comprising:

a plurality of tail rotors rotatably coupled to the tailboom; and

a flight control computer including a processor implementing a tail rotor balancing module including a tail rotor balancing monitoring module and a tail rotor balancing command module;

wherein, the processor implements the tail rotor balancing monitoring module to detect an airspeed of the helicopter and to identify a first set of one or more tail rotors in the plurality of tail rotors in response to the airspeed of the helicopter exceeding a first airspeed threshold; and

wherein, the processor implements the tail rotor balancing command module to reduce a rotational speed of the first set of one or more tail rotors.

2. The electrically distributed yaw control system as recited in claim 1 wherein the tail rotor balancing monitoring module further comprises a rotational speed monitoring module;

wherein, the processor implements the rotational speed monitoring module to identify a second set of one or more tail rotors in the plurality of tail rotors having a rotational speed exceeding a rotational speed threshold; and

wherein, the processor implements the tail rotor balancing command module to reduce the rotational speed of the second set of one or more tail rotors and increase a rotational speed of a third set of one or more tail rotors in the plurality of tail rotors, the second set of one or more tail rotors different than the third set of one or more tail rotors.

3. The electrically distributed yaw control system as recited in claim 1 wherein the tail rotor balancing monitoring module further comprises a power consumption monitoring module;

wherein, the processor implements the power consumption monitoring module to identify a second set of one or more tail rotors in the plurality of tail rotors having a power consumption exceeding a maximum motor power allowance; and

wherein, the processor implements the tail rotor balancing command module to reduce the power consumption of the second set of one or more tail rotors and increase a power consumption of a third set of one or more tail rotors in the plurality of tail rotors, the second set of one or more tail rotors different than the third set of one or more tail rotors.

4. The electrically distributed yaw control system as recited in claim 1 wherein the tail rotor balancing monitoring module further comprises a power consumption monitoring module;

wherein, the processor implements the power consumption monitoring module to determine whether the tail rotors have a collective power consumption exceeding a total generated power threshold and to identify a second set of one or more tail rotors in the plurality of tail rotors in response to the collective power consumption exceeding the total generated power threshold; and

wherein, the processor implements the tail rotor balancing command module to reduce a power consumption of the second set of one or more tail rotors.

5. The electrically distributed yaw control system as recited in claim 1 wherein the tail rotor balancing monitoring module further comprises a torque monitoring module;

wherein, the processor implements the torque monitoring module to identify a second set of one or more tail rotors in the plurality of tail rotors having a torque exceeding a torque threshold; and

wherein, the processor implements the tail rotor balancing command module to reduce the torque of the second set of one or more tail rotors and increase a torque of a third set of one or more tail rotors in the plurality of tail rotors, the second set of one or more tail rotors different than the third set of one or more tail rotors.

6. The electrically distributed yaw control system as recited in claim 1 wherein the tail rotor balancing monitoring module further comprises a load monitoring module;

wherein, the processor implements the load monitoring module to identify a second set of one or more tail rotors in the plurality of tail rotors experiencing a load exceeding a tail rotor load threshold; and

wherein, the processor implements the tail rotor balancing command module to reduce the load of the second set of one or more tail rotors and increase a load of a third set of one or more tail rotors in the plurality of tail rotors, the second set of one or more tail rotors different than the third set of one or more tail rotors.

7. The electrically distributed yaw control system as recited in claim 1 wherein the tail rotor balancing monitoring module further comprises a flight mode monitoring module;

wherein, the processor implements the flight mode monitoring module to detect a flight mode of the helicopter, the helicopter having a plurality of flight modes including a forward flight mode and a hover mode, and to identify a second set of one or more tail rotors in the plurality of tail rotors based on the flight mode of the helicopter; and

wherein, the processor implements the tail rotor balancing command module to reduce a rotational speed of the second set of one or more tail rotors.

8. The electrically distributed yaw control system as recited in claim 7 wherein the processor implements the tail rotor balancing command module to deactivate the second set of one or more tail rotors.

9. The electrically distributed yaw control system as recited in claim 7 wherein the processor implements the tail rotor balancing command module to increase a rotational speed of a third set of one or more tail rotors in the plurality of tail rotors, the second set of one or more tail rotors different than the third set of one or more tail rotors.

10. The electrically distributed yaw control system as recited in claim 1 wherein the tail rotor balancing monitoring module further comprises a maneuver detection module;

wherein, the processor implements the maneuver detection module to detect a maneuver being performed by the helicopter and to identify a second set of one or more tail rotors in the plurality of tail rotors based on the maneuver; and

wherein, the processor implements the tail rotor balancing command module to reduce a rotational speed of the second set of one or more tail rotors.

11. The electrically distributed yaw control system as recited in claim 1 wherein the processor implements the airspeed monitoring module to identify a second set of one or more tail rotors in the plurality of tail rotors in response to the airspeed of the helicopter being less than a second airspeed threshold; and

wherein, the processor implements the tail rotor balancing command module to reduce a rotational speed of the second set of one or more tail rotors.

12. A rotorcraft comprising:

a fuselage;

a tailboom extending from the fuselage, the tailboom having an aft portion; and

an electrically distributed yaw control system comprising:

a shroud coupled to the aft portion of the tailboom and forming one or more ducts;

a plurality of tail rotors disposed in the one or more ducts; and

a flight control computer including a processor implementing a tail rotor balancing module including a tail rotor balancing monitoring module and a tail rotor balancing command module;

wherein, the processor implements the tail rotor balancing monitoring module to detect an airspeed of the helicopter and to identify a first set of one or more tail rotors in the plurality of tail rotors in response to the airspeed of the helicopter exceeding a first airspeed threshold; and

wherein, the processor implements the tail rotor balancing command module to reduce a rotational speed of the first set of one or more tail rotors.

13. The rotorcraft as recited in claim 12 wherein each tail rotor further comprises a motor;

wherein, the tail rotor balancing monitoring module further comprises a motor failure detection module;

wherein, the processor implements the motor failure detection module to identify a second set of one or more tail rotors in the plurality of tail rotors experiencing a motor failure; and

wherein, the processor implements the tail rotor balancing command module to deactivate the second set of one or more tail rotors and increase a rotational speed of a third set of one or more tail rotors in the plurality of tail rotors, the second set of one or more tail rotors different than the third set of one or more tail rotors.

14. The rotorcraft as recited in claim 12 wherein the tail rotor balancing monitoring module further comprises an airframe stability monitoring module;

wherein, the processor implements the airframe stability monitoring module to monitor an excitation frequency of the tail rotors and to identify a second set of one or more tail rotors in the plurality of tail rotors in response to the excitation frequency being within a frequency threshold of a natural frequency of an airframe component of the rotorcraft; and

wherein, the processor implements the tail rotor balancing command module to modify a rotational speed of the second set of one or more tail rotors.