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.
Plasma actuating propulsion system for aerial vehicles and propulsion method thereof
Plasmaantrieb-System in einem Luftfahrzeug und Antriebsverfahren dazu
Système de propulsion plasma pour véhicules aériens et son procédé de propulsion
2018-12-19
Patent
Electronic Resource
English