Abstract
Hall Effect thrusters (HET) have demonstrated its applicability on satellites for the Low earth orbit (LEO), Geo-stationary earth orbit (GEO) and long duration missions. High thrust density and long lifetimes are attractive parameters of the HET. In order to improve the thruster performance and lifetimes, decades of efforts are made to understand the plasma physics. Several intrusive and non-intrusive diagnostics techniques are employed for HET investigation. Simple and precise diagnostics technique is attractive to delineate the characteristics of the thruster. Optical emission spectroscopy provides several advantages over the other methods which are used for the HET diagnostics. Using this diagnostics tool in correlation with the collisional radiative model, the information of electron kinetics is extracted instantaneously. Collisional radiative model is developed by using the xenon near-infrared emission lines. This kinetic model can be used to determine the local electron temperature with error less than 15 % for investigating the HET physics.
Highlights
Electric propulsion (EP) systems increasing use in terms of controlling commercial and military satellites is well known
Studies quantitatively specifying the errors inducing from C–R models design [7] are limited as previously the electron kinetic modeling efforts were based on theoretical codes which lead to large uncertainties in extracted plasma parameters
It is evident from the lower discrepancy between the experimental and theoretical results that the C–R model is successfully designed and its applicability is confirmed for the Hall effect thrusters (HET) plasma diagnostics
Summary
Electric propulsion (EP) systems increasing use in terms of controlling commercial and military satellites is well known. In order to improve the thruster’s performance and lifetime decades of efforts are made to understand the plasma physics. This is carried out by extracting the information of plasma parameters and correlating it, to the reference parameters (construction material and design) of the thruster as given in reference [2]. The information of electron temperature (Te) profile reveals the energetic plasma influence on thruster surface as reported in reference [3]. Further this effect of near wall Te on thruster surface is confirmed with the erosion measurement [4]. C–R model along with optical emission spectroscopy (OES) for analysis of Te in HET plasma
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callMore From: Eastern-European Journal of Enterprise Technologies
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
