Plasma actuating propulsion system for aerial vehicles and propulsion method thereof

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...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	Liu, Shengyi, Khozikov, Vyacheslav
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AEROPLANES AIRCRAFT AVIATION BLASTING COSMONAUTICS ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR ELECTRICITY HEATING HELICOPTERS LIGHTING MACHINES OR ENGINES FOR LIQUIDS MECHANICAL ENGINEERING OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR PERFORMING OPERATIONS PLASMA TECHNIQUE PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDEDFOR PRODUCING MECHANICAL POWER PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OFNEUTRONS PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMICBEAMS TRANSPORTING WEAPONS WIND, SPRING WEIGHT AND MISCELLANEOUS MOTORS
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Beschreibung
Zusammenfassung:	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.