Plasma actuating propulsion system for aerial vehicles
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 a periodic 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.
1. A cascaded dielectric barrier discharge device for accelerating an air flow for propelling a vehicle, comprising:
a nozzle having upstream and downstream ends;
a dielectric barrier layer along the entire inside periphery of the nozzle;
a first annular electrode around the inside periphery of the upstream end of the nozzle and external to the dielectric barrier layer;
a second annular electrode around the inside periphery of the nozzle, downstream of the first annular electrode, and internal to the dielectric barrier layer; and
a plurality of annular electrodes around the inside periphery of the nozzle, downstream of the first and second annular electrodes, internal to the dielectric barrier layer, and in cascading clusters terminating at the nozzle downstream end.
2. The dielectric barrier discharge device of claim 1 , further comprising a high voltage source for supplying a high voltage signal to the first, second and plurality of annular electrodes.
3. The cascaded dielectric barrier discharge device of claim 2 wherein the high voltage signal is a periodic signal on the voltage source between 0.01-30 kHz.
4. The cascaded dielectric barrier discharge device of claim 2 wherein the voltage source supplies between 200 volts and 2 kV.
5. The dielectric barrier discharge device of claim 1 , wherein said first, second, and plurality of electrodes cooperate to generate a plasma field in said nozzle that creates an induced air flow within said nozzle, said induced air flow adapted to accelerate said fluid flow as said air flow moves through said nozzle.
6. The dielectric barrier discharge device of claim 1 , wherein a rapid polarity change applied to said first, second, and plurality of electrodes directionally accelerates said plasma field producing thrust through ionic wind.
7. The cascaded dielectric barrier discharge device of claim 1 wherein the annular electrodes are between 200 microns and 1 millimeter in thickness.
8. The cascaded dielectric barrier discharge device of claim 1 wherein the dielectric barrier layer is between 20 to 200 microns in thickness.