Experimental studies of the ion plasma thruster for very low orbit spacecraft

Experimental studies of the characteristics of a plasma thruster by C10H20O and background gas in a vacuum chamber have been carried out. The plasma was studied using complex diagnostics, which used a Langmuir probe and a Faraday cylinder. The degree of ionization of the plasma jet was determined by the ratio of the data from the Langmuir probe and the Faraday cylinder. The input power was measured by current and discharge voltage. The efficiency was calculated as the ratio of the output power to the input power of the beam. The resulting thrust was determined through the plasma jet current. An analysis of the operating parameters confirmed the fundamental suitability of the thruster for use as a propulsion system for an ultra-low-orbit spacecraft. Experimental studies of the plasma thruster parameters allowed us to establish the basic patterns of their relationship for further development of a physical, mathematical and simulation model.
EDN: JFYCQV, https://elibrary/jfycqv

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