Experimental Performance Characterization of a Novel Direct Current Cold Cathode Neutralizer for Electric Thruster Applications

Abstract

The 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. Nomenclature αExtraction 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

Direct Current Plasma Electron Source for Electric Propulsion Applications Using Atomic and Molecular Propellants

“…A plasma cathode does not rely on a thermionic emissive material and, instead, relies on ionization and electron generation in the bulk plasma [11]. Depending on the type of discharge, plasma cathodes can be grouped in radio frequency (RF) cathodes, capacitively coupled plasma (CCP) [12] and inductively couple plasma (ICP) [13], [14], microwave cathodes [15], [16], electron cyclotron resonance (ECR) cathodes [17], helicon cathodes [18], and direct current (DC) cathodes [19].…”