Plasma actuating propulsion system for aerial vehicles
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United States of America Patent
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Feb 3, 2015
Grant Date -
Jul 11, 2013
app pub date -
Jan 9, 2012
filing date -
Jan 9, 2012
priority date (Note) -
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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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