A space vehicle application using 5,000-kw input laser power was conceptually evaluated. A detailed design evaluation of a 10-kw experimental thruster including plasma size, chamber size, cooling, and performance analyses, was performed for 50 psia chamber pressure and using hydrogen as a propellant. The 10-kw hardware fabricated included a water cooled chamber, an uncooled copper chamber, an injector, igniters, and a thrust stand. A 10-kw optical train was designed.


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    Titel :

    Laser-heated rocket thruster


    Beteiligte:
    Shoji, J. M. (Autor:in)

    Erscheinungsdatum :

    1977-04-12


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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