Experimental study of energy balance for an electro-rocket thruster with an anode layer and power up to 1000 W

Autor:	A. V. Pil’nikov, D. N. Alekseev, M. K. Marakhtanov, V. V. Sinyavskii
Rok vydání:	2014
Předmět:	business.product_category Ion beam Chemistry Analytical chemistry Energy Engineering and Power Technology Mechanics Anode Magnetic field Nuclear Energy and Engineering Heat flux Rocket Physics::Plasma Physics Pulsed inductive thruster business Voltage drop Beam (structure)
Zdroj:	Thermal Engineering. 61:993-997
ISSN:	1555-6301 0040-6015
Popis:	Experimental results and a procedure for determining the total energy balance for single-stage thrusters with azimuth electron drift are presented. A single-stage thruster with an anode layer (TAL) with power of 200–800 W was used as an experimental model. Working medium was xenon. The near-anode potential drop was determined experimentally. The mean energy of beam ions was also determined by using a retarding field method and by integrating the retarding performances. The total ion beam current and power (useful power of TAL) are determined. The investigations are performed under minimal heat flux to an anode and for two geometries of magnetic system’s poles, which characterize different longitudinal gradients of magnetic field induction in a gas-discharge channel. It is revealed experimentally that thruster’s efficiency drops if the gradient of magnetic field induction in the channel increases. The results of investigation can be spread to more powerful thrusters.
Databáze:	OpenAIRE
Externí odkaz:	https://explore.openaire.eu/search/publication?articleId=doi_________::c4d4025d6fba09e565e738f2d47f0ce3 https://doi.org/10.1134/s004060151414002x Zobrazit plný text záznamu Full text from SpringerLink