The laser rocket systems investigated in this study were for orbital transportation using space-based, ground-based and airborne laser transmitters. The propulsion unit of these systems utilizes a continuous wave (CW) laser beam focused into a thrust chamber which initiates a plasma in the hydrogen propellant, thus heating the propellant and providing thrust through a suitably designed nozzle and expansion skirt. The specific impulse is limited only by the ability to adequately cool the thruster and the amount of laser energy entering the engine. The results of the study showed that, with advanced technology, laser rocket systems with either a space- or ground-based laser transmitter could reduce the national budget allocated to space transportation by 10 to 345 billion dollars over a 10-year life cycle when compared to advanced chemical propulsion systems (LO2-LH2) of equal capability. The variation in savings depends upon the projected mission model.


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    Titel :

    Laser rocket system analysis


    Beteiligte:
    Jones, W. S. (Autor:in) / Forsyth, J. B. (Autor:in) / Skratt, J. P. (Autor:in)

    Erscheinungsdatum :

    1979-03-15


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Laser Rocket System Analysis

    W. S. Jones / J. B. Forsyth / J. P. Skratt | NTIS | 1979



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    T. Andreev | NTIS | 1974


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    Phipps, C.R. / Luke, J.R. / McDuff, G.G. et al. | Tema Archiv | 2003


    LASER ROCKET ENGINE (VERSIONS)

    BIKMUCHEV AJDAR RUSTAMOVICH / KRJUCHKOV BORIS IVANOVICH / KORZUN VALERIJ GEORGIEVICH et al. | Europäisches Patentamt | 2015

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