Investigation was conducted to determine optimum discharge chamber configuration of 15-cm-diam, mercury-bombardment thruster for SERT (Space Electric Rocket Test) II mission; thruster used thermionic, oxide magazine cathode and permanent magnets; systematic variation of magnetic field shape and strength, propellant introduction mode, and ion extraction system determined final configuration which provided thruster operation at 0.25 amp beam current and 3000 v net accelerating potential at propellant utilization efficiencies in excess of 90% for some operating conditions; other findings.


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    Title :

    Discharge chamber optimization of SERT II thruster


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1968


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :