Tail rotor configurations for rotorcraft yaw control systems

1. A yaw control system coupled to a tailboom of a helicopter, the yaw control system comprising:

a shroud forming a plurality of ducts;

one or more stators disposed in each duct;

a plurality of tail rotors including a clockwise tail rotor and a counterclockwise tail rotor, each tail rotor secured in one of the plurality of ducts by the one or more stators and including a plurality of tail rotor blades; and

a flight control computer implementing a tail rotor blade clearance monitoring module configured to detect a clearance distance between the tail rotor blades and the one or more stators of each duct and an airframe protection command module configured to modify one or more operating parameters of the tail rotors based on the clearance distance;

wherein, the clockwise tail rotor is configured to rotate in a first rotational direction; and

wherein, the counterclockwise tail rotor is configured to rotate in a second rotational direction, the second rotational direction opposite of the first rotational direction.

2. The yaw control system as recited in claim 1 wherein the clockwise tail rotor further comprises a plurality of clockwise tail rotors and the counterclockwise tail rotor further comprises a plurality of counterclockwise tail rotors.

3. The yaw control system as recited in claim 1 wherein the clockwise and counterclockwise tail rotors are configured to emit thrust in a same direction.

4. The yaw control system as recited in claim 1 wherein the clockwise and counterclockwise tail rotors are configured to emit thrust in opposite directions.

5. The yaw control system as recited in claim 1 wherein the plurality of tail rotors include a first tail rotor having rotor blades with equidistant blade spacing and a second tail rotor having rotor blades with nonuniform blade spacing.

6. The yaw control system as recited in claim 1 wherein the plurality of tail rotors comprise a plurality of variable speed tail rotors including variable pitch rotor blades.

7. The yaw control system as recited in claim 1 wherein each tail rotor is rotatable in a single rotational direction.

8. The yaw control system as recited in claim 1 wherein the plurality of tail rotors include a first tail rotor having fixed pitch rotor blades and a second tail rotor having variable pitch rotor blades.

9. The yaw control system as recited in claim 1 wherein the plurality of tail rotors include a first tail rotor having rotor blades with a first blade twist and a second tail rotor having rotor blades with a second blade twist, the first blade twist different from the second blade twist.

10. The yaw control system as recited in claim 1 wherein the plurality of tail rotors include a first tail rotor having rotor blades with a first airfoil shape and a second tail rotor having rotor blades with a second airfoil shape, the first airfoil shape different from the second airfoil shape.

11. The yaw control system as recited in claim 1 wherein the plurality of tail rotors include a first tail rotor having a motor of a first size and a second tail rotor having a motor of a second size, the first motor size different from the second motor size.

12. The yaw control system as recited in claim 1 wherein the plurality of tail rotors include a first tail rotor having rotor blades formed from a first material and a second tail rotor having rotor blades formed from a second material, the first material different from the second material.

13. The yaw control system as recited in claim 1 further comprising a vertical fin comprising a top vertical fin portion coupled to a top side of the shroud and a bottom vertical fin portion coupled to a bottom side of the shroud;

wherein, the bottom vertical fin portion of the vertical fin comprises a takeoff and landing bumper.

14. The yaw control system as recited in claim 1 wherein the plurality of tail rotors consists of four tail rotors and the plurality of ducts consists of four ducts.

15. The yaw control system as recited in claim 1 wherein the airframe protection command module is configured to modify the one or more operating parameters of the tail rotors in response to the clearance distance being less than a minimum tail rotor blade clearance threshold.

16. The yaw control system as recited in claim 1 wherein the clearance distance between the tail rotor blades and the one or more stators of each duct is perpendicular to the rotational plane of the tail rotor blades such that the clearance distance is proportional to bending of the tail rotor blades.

17. A rotorcraft comprising:

a fuselage;

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

a yaw control system coupled to the aft portion of the tailboom, the yaw control system comprising:

a shroud forming a plurality of ducts;

one or more stators disposed in each duct;

a plurality of tail rotors including a clockwise tail rotor and a counterclockwise tail rotor, each tail rotor secured in one of the plurality of ducts by the one or more stators and including a plurality of tail rotor blades; and

a flight control computer implementing a tail rotor blade clearance monitoring module configured to detect a clearance distance between the tail rotor blades and the one or more stators of each duct and an airframe protection command module configured to modify one or more operating parameters of the tail rotors based on the clearance distance;

wherein, the clockwise tail rotor is configured to rotate in a first rotational direction; and

wherein, the counterclockwise tail rotor is configured to rotate in a second rotational direction, the second rotational direction opposite of the first rotational direction.

18. The rotorcraft as recited in claim 17 wherein the yaw control system further comprises an electrically distributed yaw control system.

19. The rotorcraft as recited in claim 17 wherein the plurality of tail rotors collectively form a rhombus shape configuration and include an upper forward tail rotor, a lower forward tail rotor, an upper aft tail rotor and a lower aft tail rotor; and

wherein, the upper and lower forward tail rotors are vertically offset, the upper and lower aft tail rotors are vertically offset, the upper forward tail rotor is substantially horizontally aligned with the upper aft tail rotor and the lower forward tail rotor is substantially horizontally aligned with the lower aft tail rotor.