A Hall Effect Thruster fueled by xenon was duration tested for7,198 hours at NASA’s Glenn Research Center.The thruster generated 1 million Newton-seconds of total impulse before the test was terminated voluntarily. Thrust, flow rate, and many other parameters were tracked continuously. Over 98.5% of the test was conducted at a single operating point, where the discharge power was 600 W, mean thrust was 39 mN and mean specific impulse was 1500 s. The shape of the discharge channel was measured via laser profilometery. The shape changed considerably over the course of the test, due to ion sputtering. However, the standard deviation of the thrust and specific impulse measurements at the nominal operating point was less than 1%. Evolution of the plasma plume was measured with a Faraday probe mounted upon a rotating arm. Plume divergence decreased over the course of the test


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    Title :

    One Million Newton-Second Duration Test of a 600 Watt Hall Effect Thruster Fueled By Xenon


    Contributors:
    James Szabo (author) / Lawrence Byrne (author) / Mike Strain (author) / Surjeet Paintal (author) / Samuel Sawyer (author) / Terry Yu (author) / George Kolencik (author) / Vlad Hruby (author) / Timothy Gray (author) / Dean Petters (author)

    Conference:

    AIAA Propulsion and Energy 2020 ; 2020 ; Remote, US


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English