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.


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    Titel :

    Seeded gas thrusters and related system components


    Beteiligte:
    Poole, J. W. (Autor:in) / Thorpe, M. L. (Autor:in)

    Erscheinungsdatum :

    01.01.1974


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Seeded gas thrusters and related system components

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


    Seeded Gas Thrusters and Related System Components

    J. W. Poole / M. L. Thorpe | NTIS | 1974


    Hydrocarbon-Seeded Ignition System for Small Spacecraft Thrusters using Ionic Liquid Propellants

    Whitmore, S. / Merkley, D. / Eilers, S. et al. | British Library Conference Proceedings | 2013