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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    Titel :

    Electrothermal Thruster Diagnostics. Volume 2: Technical


    Beteiligte:
    S. Zafran (Autor:in) / B. Jackson (Autor:in)

    Erscheinungsdatum :

    1983


    Format / Umfang :

    57 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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