LOW PRESSURE DIELECTRIC BARRIER DISCHARGE PLASMA THRUSTER

Some embodiments of the invention include a thruster system comprising a thruster and a pulsing power supply. The thruster may include a gas inlet port; a plasma jet outlet; and a first electrode. In some embodiments, the pulsing power supply may provide an electrical potential to the first electrod...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	Hashim, Akel, Carscadden, John G, Slobodov, Ilia, Ziemba, Timothy M, Miller, Kenneth E, Picard, Julian F, Prager, James R
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR ELECTRICITY HEATING LIGHTING MACHINES OR ENGINES FOR LIQUIDS MECHANICAL ENGINEERING OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR 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 WEAPONS WIND, SPRING WEIGHT AND MISCELLANEOUS MOTORS
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Beschreibung
Zusammenfassung:	Some embodiments of the invention include a thruster system comprising a thruster and a pulsing power supply. The thruster may include a gas inlet port; a plasma jet outlet; and a first electrode. In some embodiments, the pulsing power supply may provide an electrical potential to the first electrode with a pulse repetition frequency greater than 10 kHz, a voltage greater than 5 kilovolts. In some embodiments, the pressure downstream from the thruster can be less than 10 Torr. In some embodiments, when a plasma is produced within the thruster by energizing a gas flowing into the thruster through the gas inlet port, the plasma is expelled from the thruster through the plasma jet outlet.