Fluidic pitch control systems for use in forward flight
An active flow control system for generating pitch control moments for an aircraft during flight. The system includes a nozzle disposed proximate the aft end of the aircraft. The nozzle is configured to discharge a gas stream in the aftward direction. A pressurized air system includes a pressurized air source and one or more injectors configured to selectively inject pressurized air into the nozzle to influence the path of the gas stream. Based upon which injectors are injecting pressurized air into the nozzle, the gas stream exits the nozzle generating no pitch control moment, generating a pitch down control moment or generating a pitch up control moment.
1. An active flow control system for generating pitch control moments for an aircraft during flight, the aircraft having an aft end, the system comprising:
a flat diverging nozzle disposed proximate the aft end of the aircraft, the nozzle having an upper surface, a lower surface, an upper expansion ramp and a lower expansion ramp, the nozzle configured to discharge a gas stream in an aftward direction; and
a pressurized air system including a pressurized air source coupled to a plurality of injectors, the plurality of injectors including an upper injector coupled to the upper surface of the nozzle and a lower injector coupled to the lower surface of the nozzle, the upper and lower injectors configured to selectively inject pressurized air in the nozzle substantially transverse to the flow of the gas stream, such that when neither the upper injector nor the lower injector is injecting pressurized air into the nozzle, the gas stream exits the nozzle generating no pitch control moment, when the upper injector is injecting pressurize air into the nozzle, the gas stream is diverted toward the lower expansion ramp generating a pitch down control moment and when the lower injector is injecting pressurize air into the nozzle, the gas stream is diverted toward the upper expansion ramp generating a pitch up control moment.
2. The system as recited in claim 1 wherein the gas stream further comprises a propulsive gas stream formed from bypass air combined with engine exhaust that generates forward thrust.
3. The system as recited in claim 1 wherein the upper and lower injectors are configured to selectively inject the pressurized air into the nozzle normal to the flow of the gas stream.
4. The system as recited in claim 1 wherein the pressurized air source further comprises a compressor.
5. The system as recited in claim 1 wherein each of the injectors further comprises one or more slots.
6. The system as recited in claim 1 wherein each of the injectors further comprises a plurality of jets.
7. An active flow control system for generating pitch control moments for an aircraft during flight, the aircraft having an aft end, the system comprising:
a diverging nozzle disposed proximate the aft end of the aircraft, the nozzle having upper and lower surfaces and a lower expansion ramp, the nozzle configured to discharge a gas stream in an aftward direction; and
a pressurized air system including a pressurized air source coupled to an injector, the injector coupled to the lower surface of the nozzle, the injector configured to selectively inject pressurized air into the nozzle substantially transverse to the flow of the gas stream, such that when the injector is not injecting pressurized air into the nozzle, the gas stream attaches to the lower expansion ramp generating a pitch down control moment, when the injector is injecting pressurize air into the nozzle at a first intensity, the gas stream is diverted away from the lower expansion ramp generating no pitch control moment and wherein, when the injector is injecting pressurize air into the nozzle at a second intensity that is greater than the first intensity, the gas stream is diverted away from the lower expansion ramp generating a pitch up control moment.
8. The system as recited in claim 7 wherein the nozzle further comprises a flat nozzle.
9. The system as recited in claim 7 wherein the gas stream further comprises a propulsive gas stream formed from bypass air combined with engine exhaust that generates forward thrust.
10. The system as recited in claim 7 wherein the injector is configured to selectively inject the pressurized air into the nozzle normal to the flow of the gas stream.
11. The system as recited in claim 7 wherein the pressurized air source further comprises a compressor.
12. The system as recited in claim 7 wherein the injector further comprises one or more slots.
13. The system as recited in claim 7 wherein the injector further comprises a plurality of jets.
14. 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.
15. The system as recited in claim 14 wherein the pressurized air system further comprises a valve system disposed between the air manifold and the injectors.
16. The system as recited in claim 15 wherein the pressurized air system further comprises a controller system configured to operate the valve system.
17. The system as recited in claim 16 wherein the pressurized air system further comprises an active flow control module configured to provide commands to the controller system.
18. The system as recited in claim 17 further comprising a flight control system configured to execute the active flow control module.
19. The system as recited in claim 1 wherein the pressurized air source further comprises a compressor driven by a turboshaft engine.
20. The system as recited in claim 1 wherein the pressurized air system is configured to inject variable intensity pressurized air such that the upper and lower injectors generate pitch control moments of variable intensity to control the rate of pitch maneuvers of the aircraft.