Propulsive anti-torque nozzle system with external rotating sleeve for a rotorcraft

1. A propulsive anti-torque system for an aircraft, the propulsive anti-torque system comprising:

a system duct in fluid communication with a tailboom duct, the system duct having a downstream portion with an anti-torque cutout and a pro-torque cutout;

an anti-torque nozzle exteriorly proximate to the anti-torque cutout;

a pro-torque nozzle exteriorly proximate to the pro-torque cutout;

a rotating sleeve configured to selectively allow airflow into at least one of the anti-torque nozzle and the pro-torque nozzle;

a thrust nozzle in fluid communication with the system duct;

an upper clamshell and a lower clamshell, each selectively controlled to contribute to pitch control and forward thrust, each controlled by a separate actuator so as to operate asymmetrically to alter the airflow through the system duct, the upper clamshell and lower clamshell having a curved shaped concaved to the flow of air so as to generate an upward thrust vector and a downward thrust vector.

2. The propulsive anti-torque system according to claim 1 , wherein the rotating sleeve is concentric to the system duct.

3. The propulsive anti-torque system according to claim 1 , wherein the airflow through the thrust nozzle produces a forward thrust vector on the aircraft.

4. The propulsive anti-torque system according to claim 1 , wherein the airflow through the anti-torque nozzle produces an anti-torque vector, thereby producing a torque on the aircraft.

5. The propulsive anti-torque system according to claim 1 , wherein the airflow through the pro-torque nozzle produces a pro-torque vector, thereby producing a torque on the aircraft.

6. The propulsive anti-torque system according to claim 1 , wherein the airflow through the anti-torque nozzle and the thrust nozzle produces a resultant force which is a combination of an anti-torque vector and a thrust vector.

7. The propulsive anti-torque system according to claim 1 , wherein the airflow is pressurized by an engine and a fan.

8. The propulsive anti-torque system according to claim 1 , wherein the anti-torque nozzle comprises:

at least one anti-torque vane for directing the airflow in an anti-torque producing direction.

9. The propulsive anti-torque system according to claim 1 , wherein the pro-torque nozzle comprises:

at least one pro-torque vane for directing the airflow in a pro-torque producing direction.

10. The propulsive anti-torque system according to claim 1 , wherein the rotating sleeve is exterior to the system duct.

11. The propulsive anti-torque system according to claim 1 , wherein the upper clamshell and the lower clamshell are configured to be actuated independently.

12. The propulsive anti-torque system according to claim 1 , wherein the thrust nozzle is configured to produce an upward thrust vector when the lower clamshell is closed and the upper clamshell is open, thereby producing a pitching up moment on the aircraft.

13. The propulsive anti-torque system according to claim 1 , wherein the thrust nozzle is configured to produce an downward thrust vector when the lower clamshell is open and the upper clamshell is closed, thereby producing a pitching down moment on the aircraft.

14. An aircraft comprising:

an engine which provides power to a main rotor system;

a fan;

a tailboom duct that acts as a conduit to provide airflow to a propulsive anti-torque system, the airflow being a mixture of compressed air from the fan and exhaust from the engine; and

a propulsive anti-torque system located near an aft end of the tailboom, the propulsive anti-torque system comprising:

a system duct in fluid communication with the tailboom duct, the system duct having a downstream portion with an anti-torque cutout and a pro-torque cutout;

an anti-torque nozzle exterior and proximate to the anti-torque cutout;

a pro-torque nozzle exterior and proximate to the pro-torque cutout;

a rotating sleeve configured to selectively allow airflow into at least one of the anti-torque nozzle and the pro-torque nozzle;

a thrust nozzle in fluid communication with the system duct; and

an upper clamshell and a lower clamshell, each selectively controlled to contribute to pitch control and forward thrust, each controlled by a separate actuator so as to operate asymmetrically to alter the airflow through the system duct, the upper clamshell and lower clamshell having a curved shaped concaved to the flow of air so as to generate an upward thrust vector and a downward thrust vector.

15. The aircraft according to claim 14 , wherein the airflow through the thrust nozzle produces a forward thrust vector on the aircraft.

16. The aircraft according to claim 14 , wherein the airflow through the anti-torque nozzle produces an anti-torque vector, thereby producing a torque on the aircraft.

17. The aircraft according to claim 14 , wherein the airflow through the pro-torque nozzle produces a pro-torque vector, thereby producing a torque on the aircraft.

18. The aircraft according to claim 14 , wherein the airflow through the anti-torque nozzle and the thrust nozzle produces a resultant force which is a combination of an anti-torque vector and a thrust vector.

19. The aircraft according to claim 14 , wherein the airflow is pressurized by an engine and a fan.