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One-dimensional model of a pulsed plasma thruster

Published online by Cambridge University Press:  27 January 2016

T. R. Nada
T. R. Nada*
Affiliation:
Emirates Aviation College, Dubai, UAE
*
tareknada@gmail.com
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Abstract

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This paper presents a modified one dimensional model for the pulsed plasma thruster. The model takes into account the impact of thruster geometry and capacitor initial energy on plasma inductance and resistance, as well as the ablated mass per pulse. These three factors have significant impact on the performance of the thruster and have not been considered concurrently before. The model is verified by comparing the estimated specific impulse, impulse bit and thrust-to-power ratio with experimental measurements for space qualified thrusters. The maximum error is estimated to be about 8% when using the modified model, while the conventional snowplow model produces error up to about 70%. The modified model is then employed to generate design charts that would help in selecting the proper combination of thruster geometry and energy level in the preliminary design phase of a pulsed plasma thruster for different space missions.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1195 , September 2013, pp. 929 - 942
Copyright
Copyright © Royal Aeronautical Society 2013 

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