Plasma-assisted synthetic jets for active air flow control

Patent metadata

Field	Value
Publication number	US-9637224-B2
Application number	US-201414186760-A
Country	US
Kind code	B2
Filing date	Feb 21, 2014
Priority date	Feb 21, 2014
Publication date	May 2, 2017
Grant date	May 2, 2017

Abstract

A plasma-assisted synthetic jet device, an aircraft including a plasma-assisted synthetic jet device, and a method of improving aerodynamic properties are disclosed for providing air flow control at an aerodynamic structure by ionizing one or more gases exiting through an aperture of the synthetic jet device disposed in the aerodynamic structure.

First claim

What is claimed is:

1. A plasma-assisted synthetic jet actuator, comprising:
an aerodynamic structure having an aerodynamic surface and forming an aperture through the aerodynamic surface;
one or more walls forming a chamber within the aerodynamic structure and adjacent to the aerodynamic surface, wherein the chamber is in fluid communication with an ambient environment through the aperture; and
an ionizing device disposed at the aperture and configured to ionize one or more nonionized chamber gases exiting through the aperture into the ambient environment, wherein the one or more nonionized chamber gases are propelled toward the aperture by a propulsion source distinct from the ionizing device.

2. The plasma-assisted synthetic jet actuator of claim 1 , wherein the propulsion source comprises a pressure differential between the chamber and the ambient environment.

3. The plasma-assisted synthetic jet actuator of claim 1 , wherein the propulsion source comprises a gas propulsion device configured to propel the one or more nonionized chamber gases through the aperture.

4. The plasma-assisted synthetic jet actuator of claim 3 , wherein the gas propulsion device is a piezoelectric-actuated diaphragm.

5. The plasma-assisted synthetic jet actuator of claim 1 , wherein the ionizing device comprises first and second electrodes disposed on opposing sides of the aerodynamic surface.

6. The plasma-assisted synthetic jet actuator of claim 5 , further comprising an insulating layer configured to at least partially cover one of the first and second electrodes.

7. The plasma-assisted synthetic jet actuator of claim 1 , wherein the ionized chamber gases are steerable using at least one of an actuating device configured to pivot the plasma-assisted synthetic jet actuator and one or more electromagnets disposed within the aerodynamic structure and in proximity of the plasma-assisted synthetic jet actuator.

8. The plasma-assisted synthetic jet actuator of claim 3 , further comprising a first power supply providing a first signal to the gas propulsion device, and a second power supply providing a second signal to the ionizing device, wherein the first signal is synchronized with the second signal.

9. The plasma-assisted synthetic jet actuator of claim 8 , wherein a pulse of the second signal is delayed by a predetermined amount from a pulse of the first signal, the predetermined amount based on an amount of time for a volume of the propelled one or more nonionized chamber gases to reach the aperture.

10. An aircraft, comprising:
a thrust source;
one or more lifting surfaces configured to generate a lift force when coupled to the thrust source; and
at least one plasma-assisted synthetic jet actuator configured to provide air flow control at an aerodynamic structure of the aircraft, the aerodynamic structure having an aerodynamic surface and forming an aperture through the aerodynamic surface, and the plasma-assisted synthetic jet actuator comprising:
one or more walls forming a chamber within the aerodynamic structure and adjacent to the aerodynamic surface, wherein the chamber is in fluid communication with an ambient environment through the aperture; and
an ionizing device disposed at the aperture and configured to ionize one or more nonionized chamber gases exiting through the aperture into the ambient environment, wherein the one or more nonionized chamber gases are propelled toward the aperture by a propulsion source distinct from the ionizing device.

11. The aircraft of claim 10 , wherein the the propulsion source comprises a gas propulsion device configured to propel the one or more nonionized chamber gases through the aperture.

12. The aircraft of claim 10 , further comprising one or more control surfaces, wherein the at least one plasma-assisted synthetic jet actuator is configured to augment the one or more control surfaces.

13. The aircraft of claim 11 , the synthetic jet actuator further comprising a first power supply providing a first signal to the gas propulsion device, and a second power supply providing a second signal to the ionizing device, wherein the first signal is synchronized with the second signal.

14. A method to improve aerodynamic properties of an aerodynamic structure, the method comprising:
providing air flow control at the aerodynamic structure by ionizing one or more nonionized gases exiting through an aperture formed in an aerodynamic surface of the aerodynamic structure,
wherein the air flow control is provided by a plasma-assisted synthetic jet actuator, comprising:
one or more walls forming a chamber within the aerodynamic structure and adjacent to the aerodynamic surface, wherein the chamber is in fluid communication with an ambient environment through the aperture; and
an ionizing device disposed at the aperture and configured to ionize one or more nonionized chamber gases exiting through the aperture, wherein the one or more nonionized chamber gases are propelled toward the aperture by a propulsion source distinct from the ionizing device.

15. The method of claim 14 , wherein the propulsion source comprises a gas propulsion device.

16. The method of claim 14 , wherein the aerodynamic structure is included in an aircraft, and wherein the air flow control is used to at least augment one or more control surfaces of the aircraft.

17. The method of claim 16 , wherein the aerodynamic structure is an inlet of a jet engine of the aircraft.

18. The method of claim 15 , wherein the gas propulsion device is coupled to a first power supply, and the ionizing device is coupled to a second power supply, wherein a first signal provided by the first power supply is synchronized with a second signal provided by the second power supply.

19. The aircraft of claim 10 , wherein the propulsion source comprises a pressure differential between the chamber and the ambient environment.

20. The aircraft of claim 11 , wherein the gas propulsion device is a piezoelectric-actuated diaphragm.

21. The method of claim 14 , wherein the propulsion source comprises a pressure differential between the chamber and the ambient environment.

22. The method of claim 15 , wherein the gas propulsion device is a piezoelectric-actuated diaphragm.

Assignees

• Boeing Co

Inventors

• Nikic Dejan

Classifications

• H05H1/2439

  Surface discharges, e.g. air flow control · CPC title

• Y02T50/10

  Drag reduction · CPC title

• B64C23/005

  by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds · CPC title

• B64C19/00

  Aircraft control not otherwise provided for · CPC title

• B64C2230/12

  by using electromagnetic tiles, fluid ionizers, static charges or plasma · CPC title