Invention Grant
US08944370B2 Plasma actuating propulsion system for aerial vehicles 有权
用于航空器的等离子体驱动推进系统

Plasma actuating propulsion system for aerial vehicles
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 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.
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