First phase of program of development work on plasmajet thruster suitable for attitude control and orbit adjustment of satellite is described; effort resulted in thruster capable of delivering required thrust (0.01 lb) at specific impulse in excess of 1100 sec; kinetic efficiencies in excess of 35% were obtained using hydrogen as propellant; specific design, along with other designs tested, is reported.


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    Title :

    Research and development of 1-kw plasmajet thruster


    Additional title:

    AIAA J


    Contributors:
    Greco, R.V. (author) / Stoner, W.A. (author)

    Published in:

    AIAA Journal ; 1 , n 2


    Publication date :

    1963


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    RESEARCH AND DEVELOPMENT OF A 1-KW PLASMAJET THRUSTER

    Greco, R. V. / Stoner, W. A. | NTRS | 1963


    RESEARCH AND DEVELOPMENT OF A 1-KW PLASMAJET THRUSTER

    GRECO, R. V. / STONER, W. A. | AIAA | 1963


    Micro-Multi-Plasmajet Array Thruster

    Horisawa, Hideyuki / Hagiwara, Shuji / Funaki, Ikkoh | AIAA | 2010


    RESEARCH AND DEVELOPMENT OF A 1 KW PLASMAJET THRUSTER

    Greco, R. V. / Stoner, W. A. | NTRS | 1962


    EXPERIMENTAL PLASMAJET THRUSTOR RESULTS

    MASSER, P. S. | AIAA | 1963