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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN
Vol. 7 (2009) No. ists26 (ISTS Special Issue: Selected papers from the 26th International Symposium on Space Technology and Science) P Pb_41-Pb_45

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http://doi.org/10.2322/tstj.7.Pb_41

b) Electric and Advanced Propulsion
  • Abstracts

Discharge current oscillation at the frequency range of 10-100 kHz causes serious problems in using an anode layer type Hall thruster in space. As a new approach to the discharge stabilization, azimuthally nonuniform propellant flows were created in an acceleration channel. A plenum chamber was divided into two rooms to which xenon gas was supplied at different flow rates. As a result, stable discharge was achieved in wider operation conditions with the larger mass flow differential. The oscillation amplitude at the maximum thrust efficiency was decreased by up to 94%. In addition, thrust vector was measured and the deviation angle was found to vary with the differential flow rate and magnetic flux density.

Copyright © 2009 The Japan Society for Aeronautical and Space Sciences

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