System, designed for fight testing of electrical propulsion system in Space Electric Rocket Test (SERT) program, was tested at NASA Lewis Research Center in 1962 at environmental pressure of 8×10-5 mm of mercury; current, voltage, propellant flow rate, thrust, chamber pressure, and body temperatures were measured continuously; engine efficiencies (10-30%) and specific impulses (600-1400 sec) were deduced from data, but reliability of thrust measurements was poor; exhaust plume was photographed to reveal size, turning angle, and shape of wavelength regions.


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    Title :

    1-kw arcjet-engine system-performance test


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Ducati, A.C. (author) / Humpal, H. (author) / Meltzer, J. (author) / Muehlberger, E. (author) / Waltzer, H. (author) / Todd, J.P. (author)

    Published in:

    Publication date :

    1964


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    1-kw arcjet-engine system-performance test

    DUCATI, A. C. / HUMPAL, H. / MELTZER, J. et al. | AIAA | 1964


    ARCJET ENGINE PERFORMANCE- EXPERIMENT AND THEORY

    BENNETT, S. / CONNORS, J. F. / JOHN, R. R. | AIAA | 1963


    Miniaturized Arcjet Performance Improvement

    Sankovic, J. / Hopkins, J. / American Institute of Aeronautics and Astronautics et al. | British Library Conference Proceedings | 1996



    Pulsed arcjet performance measurements

    Willmes, Gary / Burton, Rodney | AIAA | 1995