Abstract
AbstractThe development of electrostatic ion thrusters so far has mainly been based on empirical and qualitative knowhow, and on evolutionary iteration steps. This resulted in considerable effort regarding prototype design, construction and testing and therefore in significant development and qualification costs and high time demands. For future developments it is anticipated to implement simulation tools which allow for quantitative prediction of ion thruster performance, long‐term behavior and space craft interaction prior to hardware design and construction. Based on integrated numerical models combining self‐consistent kinetic plasma models with plasmawall interaction modules a new quality in the description of electrostatic thrusters can be reached. These open the perspective for predictive modeling in this field. This paper reviews the application of a set of predictive numerical modeling tools on an ion thruster model of the HEMP‐T (High Efficiency Multi‐stage Plasma Thruster) type patented by Thales Electron Devices GmbH. (© 2014 WILEY‐VCH Verlag GmbH & Co. KGaA, Weinheim)
Highlights
Ion thrusters, where the propellant is ionized and the ions are accelerated by electric fields, are of increasing importance for scientific and commercial space missions
A Monte Carlo model using a ray approximation for the particles allowsus to calculate the back-flux towards the thruster exit generated by sputtered particles at the vessel walls
It has shown the influence of the test set-up and the vessel size, which affects the re-deposition pattern inside the thruster channels
Summary
Ion thrusters, where the propellant is ionized and the ions are accelerated by electric fields, are of increasing importance for scientific and commercial space missions. This results in a considerably reduced propellant budget, and a significant reduction of spacecraft launch mass by some 100 to 1000 kg can be achieved One concept for this electric propulsion involves grid-less ion thrusters, which are based on magnetic confinement of the plasma electrons, where the trapped electrons both ionize the propellant and provide the potential drop for ion acceleration. Due to their low complexity in terms of system architecture, they are becoming of increasing interest in particular for commercial satellites.
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