A program involved with the construction and test of a number of laser heated thrusters is described. These thrusters, with a cavity approximately 23 cm long and 3.5 cm in i.d., are to be tested by NASA at a later date with a laser beam focused through the throat to heat hydrogen propellant containing an opacifier. The heated propellant exhausts through a supersonic nozzle with a 0.6 cm throat at 3000 C. Thrust stands and control systems were furnished with the thrusters. The report describes radio frequency plasma heated hot and cold flow simulation tests by the contractor. (Author)


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    Title :

    Seeded Gas Thrusters and Related System Components


    Contributors:
    J. W. Poole (author) / M. L. Thorpe (author)

    Publication date :

    1974


    Size :

    27 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Seeded gas thrusters and related system components

    Poole, John W. / Thorpe, Merle L. | TIBKAT | 1974


    Seeded gas thrusters and related system components

    Poole, J. W. / Thorpe, M. L. | NTRS | 1974


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