Fluidic roll control systems for use in forward flight

1. A propulsion and active flow control system for an aircraft including a body having a wing with a trailing edge, the aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation, the system comprising:

an engine disposed within the body, the engine having a turboshaft mode in the VTOL orientation and a turbofan mode in the forward flight orientation, the engine configured to generate engine exhaust;

a lift fan system disposed within the body, the lift fan system including at least one ducted fan;

a forced air bypass system disposed within the body, the forced air bypass system configured to generate bypass air;

a transmission disposed between the engine and the forced air bypass system, the transmission engaging the engine with the forced air bypass system when the engine is in the turbofan mode and disengaging the engine from the forced air bypass system when the engine is in the turboshaft mode;

an exhaust system coupled to the engine and the forced air bypass system;

right and left roll effectors disposed proximate the trailing edge of the wing, the right roll effector having a right diverter with upper, lower and coanda surfaces, the left roll effector having a left diverter with upper, lower and coanda surfaces; 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 substantially tangential to the upper surface of the right diverter to divert airflow across the wing downwardly, a second injector configured to selectively inject pressurized air substantially tangential to the lower surface of the right diverter to divert airflow across the wing upwardly, a third injector configured to selectively inject pressurized air substantially tangential to the upper surface of the left diverter to divert airflow across the wing downwardly and a fourth injector configured to selectively inject pressurized air substantially tangential to the lower surface of the left diverter to divert airflow across the wing upwardly;

wherein, when none of the injectors are injecting pressurized air, the right and left roll effectors generate no roll control moment;

wherein, when the first and fourth injectors are injecting pressurized air, the right and left roll effectors generate a roll left control moment; and

wherein, when the second and third injectors are injecting pressurized air, the right and left roll effectors generate a roll right control moment.

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

3. The system as recited in claim 1 wherein the right and left roll effectors form right and left slots in the trailing edge of the wing, respectively.

4. The system as recited in claim 1 wherein the right and left roll effectors are disposed proximate right and left wingtips of the wing, 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 the 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 roll effectors generate roll control moments of variable intensity to control the rate of roll maneuvers of the aircraft.

15. An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation, the aircraft comprising:

a body having a wing with a trailing edge;

an engine disposed within the body, the engine having a turboshaft mode in the VTOL orientation and a turbofan mode in the forward flight orientation, the engine configured to generate engine exhaust;

a lift fan system disposed within the body, the lift fan system including at least one ducted fan;

a forced air bypass system disposed within the body, the forced air bypass system configured to generate bypass air;

a transmission disposed between the engine and the forced air bypass system, the transmission engaging the engine with the forced air bypass system when the engine is in the turbofan mode and disengaging the engine from the forced air bypass system when the engine is in the turboshaft mode;

an exhaust system coupled to the engine and the forced air bypass system; and

an active flow control system including:

right and left roll effectors disposed proximate the trailing edge of the wing, the right roll effector having a right diverter with upper, lower and coanda surfaces, the left roll effector having a left diverter with upper, lower and coanda surfaces; 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 substantially tangential to the upper surface of the right diverter to divert airflow across the wing downwardly, a second injector configured to selectively inject pressurized air substantially tangential to the lower surface of the right diverter to divert airflow across the wing upwardly, a third injector configured to selectively inject pressurized air substantially tangential to the upper surface of the left diverter to divert airflow across the wing downwardly and a fourth injector configured to selectively inject pressurized air substantially tangential to the lower surface of the left diverter to divert airflow across the wing upwardly;

wherein, when none of the injectors are injecting pressurized air, the right and left roll effectors generate no roll control moment;

wherein, when the first and fourth injectors are injecting pressurized air, the right and left roll effectors generate a roll left control moment; and

wherein, when the second and third injectors are injecting pressurized air, the right and left roll effectors generate a roll right 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.