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.
PLASMA ACTUATING PROPULSION SYSTEM FOR AERIAL VEHICLES
2016-06-16
Patent
Electronic Resource
English
IPC: | F03H PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR , Erzeugung von Vortriebskraft [Schub] nach dem Prinzip des Rückstoßes, soweit nicht anderweitig vorgesehen / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / H05H Plasmatechnik , PLASMA TECHNIQUE |
Plasma actuating propulsion system for aerial vehicles and propulsion method thereof
European Patent Office | 2018
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