Test data taken with nitrogen, hydrogen, and ammonia propellants are presented over a wide range of operating conditions at thrust levels up to 225 mN (50 mlb). The design adaptation of a flight-qualified thruster for operation with gaseous propellant inlet is described. Post-test analysis includes evaluation of thruster performance and efficiency, and shows the effects of propellant contamination on an immersed heating element.


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    Title :

    Electrothermal thruster diagnostics. Volume 2: Technical


    Contributors:
    Zafran, S. (author) / Jackson, B. (author)

    Publication date :

    1983-05-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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