Fluidic drag rudder systems for yaw control in forward flight

1. An active flow control system for generating yaw control moments during forward flight of an aircraft having a wing with left and right wingtips, the system comprising:

right and left yaw effectors disposed proximate the right and left wingtips, respectively, the right yaw effector including upper right and lower right flow disrupters with an aftwardly extending right airfoil extension disposed therebetween and the left yaw effector including upper left and lower left flow disrupters with an aftwardly extending left airfoil extension disposed therebetween; and

a pressurized air system including a pressurized air source coupled to a plurality of injectors, the plurality of injectors including a first injector configured to selectively inject pressurized air proximate the upper right flow disrupter substantially tangential to the right airfoil extension, a second injector configured to selectively inject pressurized air proximate the lower right flow disrupter substantially tangential to the right airfoil extension, a third injector configured to selectively inject pressurized air proximate the upper left flow disrupter substantially tangential to the left airfoil extension and a fourth injector configured to selectively inject pressurized air proximate the lower left flow disrupter substantially tangential to the left airfoil extension;

wherein, when all of the injectors are injecting pressurized air, the right and left yaw effectors generate no yaw control moment;

wherein, when the first and second injectors are not injecting pressurized air, the right yaw effector generates a yaw right control moment; and

wherein, when the third and fourth injectors are not injecting pressurized air, the left yaw effector generates a yaw left control moment.

2. The system as recited in claim 1 wherein the right and left yaw effectors are symmetrically disposed on a trailing edge of the wing.

3. The system as recited in claim 1 wherein the right and left yaw effectors further comprise right and left drag rudders, respectively.

4. The system as recited in claim 1 wherein the right and left yaw effectors further comprise right and left fluidic airfoil extensions, respectively.

5. The system as recited in claim 1 wherein the pressurized air source further comprises a compressor.

6. The system as recited in claim 1 wherein the pressurized air source further comprises a compressor driven by a turboshaft engine.

7. The system as recited in claim 1 wherein each of the injectors further comprises one or more slots.

8. The system as recited in claim 1 wherein each of the injectors further comprises a plurality of jets.

9. The system as recited in claim 1 wherein the pressurized air system further comprises an air manifold disposed between the pressurized air source and the injectors.

10. The system as recited in claim 9 wherein the pressurized air system further comprises a valve system disposed between the air manifold and the injectors.

11. The system as recited in claim 10 wherein the pressurized air system further comprises a controller system configured to operate the valve system.

12. The system as recited in claim 11 wherein the pressurized air system further comprises an active flow control module configured to provide commands to the controller system.

13. The system as recited in claim 12 further comprising a flight control system configured to execute the active flow control module.

14. The system as recited in claim 1 wherein the pressurized air system is configured to inject variable intensity pressurized air such that the right and left yaw effectors generate yaw control moments of variable intensity to control the rate of yaw maneuvers of the aircraft.

15. An aircraft comprising:

a wing with left and right wingtips; and

an active flow control system including:

right and left yaw effectors disposed proximate the right and left wingtips, respectively, the right yaw effector including upper right and lower right flow disrupters with an aftwardly extending right airfoil extension disposed therebetween and the left yaw effector including upper left and lower left flow disrupters with an aftwardly extending left airfoil extension disposed therebetween; and

a pressurized air system including a pressurized air source coupled to a plurality of injectors, the plurality of injectors including a first injector configured to selectively inject pressurized air proximate the upper right flow disrupter substantially tangential to the right airfoil extension, a second injector configured to selectively inject pressurized air proximate the lower right flow disrupter substantially tangential to the right airfoil extension, a third injector configured to selectively inject pressurized air proximate the upper left flow disrupter substantially tangential to the left airfoil extension and a fourth injector configured to selectively inject pressurized air proximate the lower left flow disrupter substantially tangential to the left airfoil extension;

wherein, when all of the injectors are injecting pressurized air, the right and left yaw effectors generate no yaw control moment;

wherein, when the first and second injectors are not injecting pressurized air, the right yaw effector generates a yaw right control moment; and

wherein, when the third and fourth injectors are not injecting pressurized air, the left yaw effector generates a yaw left control moment.

16. The aircraft as recited in claim 15 wherein the aircraft further comprises a VTOL aircraft.

17. The aircraft as recited in claim 15 wherein the aircraft further comprises a low observable aircraft.

18. The aircraft as recited in claim 15 wherein the aircraft further comprises a blended wing body aircraft.

19. The aircraft as recited in claim 15 wherein the aircraft further comprises a fan-in-wing aircraft.

20. The aircraft as recited in claim 15 wherein the aircraft further comprises a fixed wing aircraft.