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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    Title :

    Laser-Heated Rocket Thruster


    Contributors:
    J. M. Shoji (author)

    Publication date :

    1977


    Size :

    187 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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