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Micro-multi-plasmajet array thruster for space propulsion applications
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DOI：10.1016/j.vacuum.2010.08.014.png)
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Abstract
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Thrust performance tests were conducted for an arrayed multi-plasmajet structure consisting of rectangular nozzle elements each with an exit height of 05 mm and length of 05 mm To evaluate the thrust characteristics of the arrayed micro-multi-plasmajet the thrust was measured using a calibrated cantilever-type thrust stand in vacuum Using 3 x 3 nozzle elements the micro-plasmajet array showed stable DC operation Compared to conditions with cold-gas flow the application of a DC discharge showed a significant improvement in thrust performance of at least 20% for thrust and specific impulse Typical values achieved for thrust specific impulse and thrust efficiency at an Input power of 6 3 W were 8 5 mN 77 s and 021 respectively (C) 2010 Elsevier Ltd All rights reserved
Keywords:
Electric Propulsion
Micro thruster
Micro multi plasmajet array
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