Of various factors that affect total efficiency available from mercury electron-bombardment ion thruster, shape of magnetic field and design of ion optical system are found to be most important; data are presented to illustrate that overall power-to-thrust ratio, including all thruster and propellant system losses, of 120 kw/lb is achievable at specific impulse of 4000 sec and mass utilization of 90 %; performance of thruster system is presented as function of mass utilization and specific impulse over range of values currently proposed for solar electric propulsion missions.


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    Title :

    Mercury electron-bombardment thruster system


    Additional title:

    J Spacecraft Rockets


    Contributors:
    King, H.J. (author)

    Published in:

    Publication date :

    1968


    Size :

    4 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



    A submillipound mercury electron bombardment thruster

    Banks, B. A. / Lathem, W. C. / Nakanishi, S. et al. | NTRS | 1970



    A sub-millipound mercury electron-bombardment thruster

    Banks, B. A. / Lathem, W. C. / Nakanishi, S. et al. | NTRS | 1970


    A sub-millipound mercury electron-bombardment thruster

    Banks, B. A. / Lathem, W. C. / Nakanishi, S. et al. | NTRS | 1970