For long range space missions, deliverable payload fraction is an inverse exponential function of the propellant exhaust velocity or specific impulse of the propulsion system. The exhaust velocity of chemical systems are limited by their combustion chemistry and heat transfer to a few km/s. Nuclear rockets may achieve double this range, but are still heat transfer limited and ponderous to develop. Various electric propulsion systems can achieve exhaust velocities in the 10 km/s range, at considerably lower thrust densities, but require an external electrical power source. A general overview is provided of the currently available electric propulsion systems from the perspective of their characteristics as a terminal load for space nuclear systems. A summary of the available electric propulsion options is shown and generally characterized in the power vs. exhaust velocity plot. There are 3 general classes of electric thruster devices: neutral gas heaters, plasma devices, and space charge limited electrostatic or ion thrusters.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Megawatt level electric propulsion perspectives


    Beteiligte:


    Erscheinungsdatum :

    01.01.1987


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch





    PEGASUS: A multi-megawatt nuclear electric propulsion system

    Coomes, Edmund P. / Cuta, Judith M. / Webb, Brent J. et al. | NTRS | 1986


    Megawatt Electric Aircraft Propulsion Power System Impedance Modelling

    Dever, Timothy P. / Kascak, Peter E. / Jansen, Ralph H. | IEEE | 2022



    Megawatt Electromagnetic Plasma Propulsion

    Gilland, James / Lapointe, Michael / Mikellides, Pavlos | NTRS | 2003