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Simulation of flows within an electrostatic ion thruster for space missions

Published online by Cambridge University Press:  04 July 2016

M. Jugroot  and
J. K. Harvey
M. Jugroot
Affiliation:
Department of Aeronautics, Imperial College of Science, Technology and Medicine, London, UK
J. K. Harvey
Affiliation:
Department of Aeronautics, Imperial College of Science, Technology and Medicine, London, UK
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Abstract

Ion thrusters are well suited for near-Earth and deep space missions because of their exceptionally high specific impulse. Those already flying are also proving to be very reliable. The flow of neutral and charged particles within the different components of these devices is very complex and although they have been studied for several years, little of the detail of their internal operation is properly understood. Numerical simulations of these flows can potentially yield an improved understanding of the physical phenomena involved and in turn this should assist in the optimising of new designs and in achieving higher specific impulses. The external plume, which can potentially cause damage to other spacecraft components such as solar panels, has been the object of some studies but the flow within the internal chambers where many complex phenomena are suspected to occur has been seriously neglected. For this reason the present fully kinetic neutral and charged particle simulations, which take account of the ionisation processes and the applied magnetic field, have been conducted. The studies have been made on one specific electrostatic ion thruster - the T5 model produced by the Space Department at the Defence and Evaluation Research Agency (DERA, Farnborough, UK). Two regions within the thruster have been concentrated on, namely the exit area of the hollow cathode and the main chamber.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 105 , Issue 1053 , November 2001 , pp. 613 - 618
Copyright
Copyright © Royal Aeronautical Society 2001 

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