Tail rotor cyclic control for pitch attitude adjustment

1. A tail rotor system comprising: a mast;

a yoke coupled to the mast and comprising a pair of rotors;

a swashplate disposed concentric to the mast and configured to pivot relative to the mast;

wherein the swashplate comprises:

a pivotable fixed ring; and

a rotatable ring that rotates with the mast and relative to the pivotable fixed ring; and

a collective crosshead:

movably coupled to the mast;

coupled to the swashplate via a first pair of linkages; and

coupled to the pair of rotors via a second pair of linkages.

2. The tail rotor system of claim 1 , wherein the collective crosshead comprises:

a body that is concentric with the mast and a trunnion disposed on the body, the trunnion comprising first and second shafts; and

a first mixing lever disposed on the first shaft and a second mixing lever disposed on the second shaft.

3. The tail rotor system of claim 2 , wherein:

a first linkage of the first pair of linkages is coupled between the swashplate and the first mixing lever; and

a second linkage of the first pair of linkages is coupled between the swashplate and the second mixing lever.

4. The tail rotor system of claim 2 , wherein:

a first linkage of the second pair of linkages is coupled between the first mixing lever and a first rotor of the pair of rotors; and

a second linkage of the second pair of linkages is coupled between the second mixing lever and a second rotor of the pair of rotors.

5. The tail rotor system of claim 1 , further comprising a cyclic control system, the cyclic control system comprising:

an actuator coupled to the pivotable fixed ring of the swashplate;

a swashplate support coupled to the pivotable fixed ring of the swashplate and configured to allow the swashplate to pivot; and

a swashplate drive linkage coupled between the rotatable ring and the mast and configured to transmit torque from the mast to the rotatable ring.

6. The tail rotor system of claim 5 , wherein:

the swashplate drive linkage comprises a first swashplate drive linkage, a second swashplate drive linkage, and a coupling;

wherein the first swashplate drive linkage is coupled between the rotatable ring and the second swashplate drive linkage;

the second swashplate drive linkage is coupled between the first swashplate drive linkage and the coupling; and

the coupling is disposed around the mast and is coupled to the mast to transmit torque to the rotatable ring.

7. The tail rotor system of claim 6 , where the first and second swashplate drive linkages comprise pivotable connections that allow the first and second swashplate drive linkages to articulate as the swashplate pivots.

8. The tail rotor system of claim 5 , further comprising a flight control computer configured to control a pivoting motion of the swashplate.

9. The tail rotor system of claim 8 , further comprising a switch configured for operation by a pilot and communicatively coupled to the flight control computer to control a cant of the pair of rotors.

10. The tail rotor system of claim 5 , further comprising a flight control computer configured to control the actuator of the cyclic control system to control a pivoting motion of the swashplate.

11. The tail rotor system of claim 10 , further comprising a switch configured for operation by a pilot and communicatively coupled to the flight control computer to control operation of the actuator.

12. A method of controlling a tail rotor system according to claim 1 the method comprising:

pivoting the swashplate of the tail rotor system about an axis passing through a diameter of the swashplate;

responsive to the pivoting:

moving a first linkage of a first pair of linkages coupled between the swashplate and the collective crosshead in a first direction; and

moving a second linkage of the first pair of linkages coupled between the swashplate and the collective crosshead in a second direction opposite the first direction; and

responsive to the movement of the first and second linkages, causing a plane of rotation of the pair of rotors of the tail rotor system to cant relative to a centerline of the mast.

13. The method of claim 12 , wherein the collective crosshead comprises:

a body concentric with the mast and a trunnion disposed on the body;

wherein the trunnion comprises first and second shafts;

a first mixing lever disposed on the first shaft and a second mixing lever disposed on the second shaft.

14. The method of claim 13 , wherein the tail rotor system comprises:

a first linkage of a second pair of linkages coupled between the first mixing lever and a first rotor of the pair of rotors; and

a second linkage of the second pair of linkages coupled between the second mixing lever and a second rotor of the pair of rotors.

15. The method of claim 14 , wherein the tail rotor system comprises a cyclic control system, the cyclic control system comprising:

an actuator coupled to the pivotable fixed ring;

a swashplate support coupled to the pivotable fixed ring and configured to allow the swashplate to pivot relative to the mast; and

a swashplate drive linkage coupled between the rotatable ring and the mast and configured to transmit torque from the mast to the rotatable ring.

16. The method of claim 15 , wherein the tail rotor system comprises a flight control computer communicatively coupled to the actuator to control the actuator.

17. The method of claim 16 , wherein the step of pivoting the swashplate comprises the step of extending or contracting the actuator to pivot the pivotable fixed ring.

18. The method of claim 16 , wherein a pitch of the helicopter is adjusted by the cyclic control system via adjustment of a vertical thrust vector of the tail rotor system.

19. The method of claim 16 , wherein a center of gravity envelope of the helicopter is adjusted by the cyclic control system via adjustment of a vertical thrust vector of the tail rotor system.

20. The method of claim 16 , wherein the tail rotor system generates additional downward thrust via adjustment of a vertical thrust vector of the tail rotor system.