Current electric propulsion system concepts employ number of thruster modules operating in parallel; design of optimum system is much more flexible if individual thrusters are electrically decoupled and if they operate from propellant distribution manifold rather than each requiring separate propellant reservoir; three approaches to electrical isolation are -- use of device which permits isolation while Hg is flowing, use of insulating value which provides isolation when valve is closed, or provision of separate feed storage reservoirs for each thruster; analysis based on 17-kw system for Jupiter flyby is conducted; optimum system configuration for each approach is defined.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    System concepts for liquid mercury cathode thruster


    Additional title:

    J Spacecraft Rockets


    Contributors:
    King, H.J. (author) / Molitor, J.H. (author) / Kami, S. (author)

    Published in:

    Publication date :

    1968


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    System concepts for a liquid mercury cathode thruster.

    Kami, S. / King, H. J. / Molitor, J. H. | NTRS | 1967



    System concepts for a liquid mercury cathode thruster.

    Kami, S. / King, H. J. / Molitor, J. H. | NTRS | 1968



    Development of a Liquid-Mercury Cathode Thruster System

    J. HYMAN J. R. BAYLESS / D. E. SCHNELKER / J. W. WARD AND J. SIMPKINS | AIAA | 1971