Plasma actuating propulsion system for aerial vehicles

Patent metadata

Field	Value
Publication number	US-9670913-B2
Application number	US-201414577260-A
Country	US
Kind code	B2
Filing date	Dec 19, 2014
Priority date	Jan 9, 2012
Publication date	Jun 6, 2017
Grant date	Jun 6, 2017

Abstract

A plasma propulsion nozzle incorporates a cylinder having an inlet and an outlet. A plurality of substantially cylindrical planarly disbanded electrodes with sandwiched dielectric spacers is cascaded in an array to be concentrically expanding from the inlet through an interior chamber to the outlet for a nozzle. A voltage source applies aperiodic signal with rapidly reversing polarity to the electrodes with differential phase applied to adjacent electrodes in the array creating and expelling plasma clusters at each dielectric spacer inducing flow from the nozzle outlet to produce thrust.

First claim

What is claimed is:

1. A plasma propulsion nozzle comprising:
a cylinder having an inlet and an outlet;
a plurality of substantially cylindrical electrodes;
a plurality of dielectric spacers, each dielectric spacer being sandwiched between two of the plurality of cylindrical electrodes,
wherein the plurality of cylindrical electrodes and dielectric spacers are cascaded in an array which is concentrically expanding from the inlet to the outlet forming an interior chamber having a conical shape; and,
a voltage source configured to apply a periodic signal with rapidly reversing polarity to the plurality of cylindrical electrodes with differential phase applied to adjacent electrodes in the array creating and expelling plasma clusters at each dielectric spacer and inducing flow through the outlet to produce thrust.

2. The plasma propulsion nozzle of claim 1 wherein the electrodes are between 200 microns and 1 millimeter in thickness.

3. The plasma propulsion nozzle of claim 1 wherein the dielectric spacers are between 20 to 200 microns in thickness.

4. The plasma propulsion nozzle of claim 1 wherein the periodic signal of the voltage source is between 0.01-30 kHz.

5. The plasma propulsion nozzle of claim 1 wherein the voltage source supplies between 200 volts and 2 kV.

6. A method for thrust generation with a plasma propulsion nozzle having an array of substantially cylindrical electrodes and a plurality of dielectric spacers, each dielectric spacer being sandwiched between two of the plurality of cylindrical electrodes, cascaded to be concentrically expanding from an inlet through an interior chamber to an outlet forming and interior chamber having a conical shape, comprising:
introducing air through the inlet into the interior chamber of the conical shape;
applying a periodic voltage signal with rapidly reversing polarity to the plurality of electrodes to provide a differential voltage between paired electrodes in adjacent plasma generation units;
creating torroidal plasma clusters at each plasma generation unit in a first phase; and
expelling the plasma clusters in a second phase introducing momentum change into the air in the interior chamber for exit through the outlet to produce thrust.

7. The method of claim 6 further comprising controlling thrust produced by the nozzle by varying the periodic voltage signal.

8. The method of claim 7 wherein varying the periodic voltage signal comprises varying the frequency of the periodic voltage signal.

9. The method of claim 7 wherein varying the periodic voltage signal comprises varying the wave shape of the periodic voltage signal.

10. The method of claim 7 wherein varying the periodic voltage signal comprises varying the amplitude of the periodic voltage signal.

11. An unmanned air vehicle comprising:
a blended wing body;
at least one plasma propulsion nozzle attached to the wing body having
a cylinder including an inlet and an outlet;
a plurality of substantially cylindrical electrodes;
a plurality of dielectric spacers, each dielectric spacer being sandwiched between two of the plurality of cylindrical electrodes, cascaded in an array which is concentrically expanding from the inlet to the outlet forming an interior chamber having a conical shape; and
a voltage source configured to apply a periodic signal with rapidly reversing polarity to the plurality of cylindrical electrodes with differential phase applied to adjacent electrodes in the array creating and expelling plasma clusters at each dielectric spacer inducing flow from the nozzle outlet to produce thrust.

12. The unmanned air vehicle as defined in claim 11 wherein the at least one plasma propulsion nozzle comprises a plurality of plasma propulsion nozzles mounted to an upper surface of the wing body.

13. The unmanned air vehicle as defined in claim 11 wherein the at least one plasma propulsion nozzle comprises a first plurality of plasma propulsion nozzles mounted to an upper surface of the wing body and a second plurality of plasma propulsion nozzles mounted to a lower surface of the wing body.

14. The unmanned air vehicle as defined in claim 11 wherein the at least one plasma propulsion nozzle is mounted in a nozzle bay in the wing body.

15. The unmanned air vehicle as defined in claim 11 wherein the at least one plasma propulsion nozzle comprises two plasma propulsion nozzles, one mounted on each wing tip of the wing body.

Assignees

• Boeing Co

Inventors

• Khozikov Vyacheslav
• Liu Shengyi

Classifications

• H05H1/2439

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

• F03H1/0081 Primary

  Electromagnetic plasma thrusters · CPC title

• F03H1/0012 Primary

  Means for supplying the propellant · CPC title

• F03H1/0037

  Electrostatic ion thrusters · 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