Influence of Azimuthally Nonuniform Propellant Flow Rate on Thrust Vector and Discharge Current Oscillation in a Hall Thruster

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Abstract

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.

Journal

  • TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7(ists26), Pb_41-Pb_45, 2009

    THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

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