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Determination of the thrust of an ion thruster by the aerodynamic method of double angle (AMαβ-method)

This paper presents the results of an experimental study of the jet thrust of a mixed jet of neutral and ionized nitrogen flowing from the working chamber of an experimental sample of an accelerator ion thruster into a vacuum space. The main method of the study was the aerodynamic double angle metho...

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Bibliographic Details
Published in:Journal of physics. Conference series 2022-03, Vol.2182 (1), p.12100
Main Authors: Vavilov, I S, Yachmenev, P S, Zharikov, K I, Fedyanin, V V, Lukyanchik, A I, Stepen’, P V
Format: Article
Language:English
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Summary:This paper presents the results of an experimental study of the jet thrust of a mixed jet of neutral and ionized nitrogen flowing from the working chamber of an experimental sample of an accelerator ion thruster into a vacuum space. The main method of the study was the aerodynamic double angle method (AMαβ-method). The method of determining low thrust and the design of the stand for the implementation of the AMαβ-method are proposed. The object of research is a prototype of an accelerator two-phase ion thruster with a solid-state microwave plasma generator and a toroidal resonator. The study showed that a 2.5 W microwave generator together with a 2.5 W accelerating potential difference voltage source with a nitrogen consumption of 0.05 -1 mg/s can increase the speed of the working gas by 2.3 times. The jet thrust, according to the test results, was 1-3.6 μN. It is shown that the thrust components (the gas-dynamic component, the ion component of a high-frequency discharge, the ion component of a glow discharge) have different levels depending on the mass flow rate of the gas.
ISSN:1742-6588
1742-6596
DOI:10.1088/1742-6596/2182/1/012100