52nd AIAA/SAE/ASEE Joint Propulsion Conference
2016; Linguagem: Inglês
10.2514/mjpc16
AutoresAntonio Gurciullo, Alexander Knoll, Paolo Bianco,
Tópico(s)Rocket and propulsion systems research
ResumoThe performance of a novel neutralizer for space applications based on a E × B discharge is presented.Preliminary tests were carried out with argon gas and flow rates in the range of 5-10 SCCM.Electrons were extracted through an orifice of diameter 1.8 mm.The maximum extracted current versus input power reported was 2.4 mA/W.The total power input, given by the sum of discharge power plus the extraction power, was in the range of 40-90 W.During extraction tests, the discharge current was limited at 0.2 A due to limit in the cooling system.Future work will be focused on tests at various extraction orifice diameters and cathode materials.Ultimately, xenon and non-conventional gases would be tested as working gases. Nomenclatureα Extraction efficiency B Magnetic field density E Electric field H Energy efficiency parameter, given by extracted current versus input power I cathode Cathode current, or discharge current I collector Collector current, or electron extraction current P cathode Power supplied to the cathode, or discharge power P collector Power supplied to the collector, or extraction power
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