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...

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Bibliographic Details
Main Authors LIU, SHENGYI, KHOZIKOV, VYACHESLAV
Format Patent
LanguageEnglish
French
German
Published 10.07.2013
Subjects
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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Summary: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.
Bibliography:Application Number: EP20130150690