Micronewton/millinewton-rit, characterization test in epl, estec
- Paper number
IAC-06-C4.P.4.05
- Author
Dr. Davar Feili, Justus-Liebig Universität Giessen, Germany
- Year
2006
- Abstract
Some new band of future esa missions need smal thrusters in two different thrust level. EO missions like EarthCare, Swarm and Earth Gravity Mission like Satellite to Satellite Tracking would require a level of few MilliNewtons down to some MicroNewtons with a thrust controllability of few µN. Formation flying missions like DARWIN and PROBA 3 and fine positioning missions necessitate strict requirements on thrust level, thrust controllability and noise, life time and reliability. The RIT technology provides a suitable benchmark to scale down the thrusters and thrust levels, as due to their principle, the electrodeless rf-ionizers might be miniaturized without mechanical problems. The Giessen EP-group undertakes in cooperation with EADS a R & D-program to develop mini RF ion thrusters. Due to its modular design, µNRIT-4 can be used with a minimum of modifications in both thrust regims. Recently this thruster has been characterized in the CORONA facility of the ESA Propulsion Laboratory in ESTEC. This paper presents the results of this test campagne including thrust controllability. As this test was performed with high precision electronic system and gas flow controller it is possible now to calculate precisely the thrust and thrust quantization. The measurements of beam profile performed with the EPL beam diagnostics system allow to determinate the divergence of the plume and the geometric factor of the thrust. The measured narrow beam divergence indicates a low risk of Spacecraft contamination.
- Abstract document
- Manuscript document
IAC-06-C4.P.4.05.pdf (🔒 authorized access only).
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