Probe to approach sun to perihelion distance of three solar radii is shown to be feasible within next two decades and will perform measurements of coronal magnetic field, coronal bulk flow patterns, and super-thermal particles; nuclear-electric propulsion with simple thrusting program will be used; final orbit is highly elliptical and does not require thrust to be applied at distances too close to sun for operation of 500-kwe SNAP-50-type nuclear-electric system; description of systems of electrically propelled spacecraft that transports sun orbiter.


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    Titel :

    Close-approach solar probe design feasibility and mission study


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Lundholm, Jr., J.G. (Autor:in) / Prohaska, E.S. (Autor:in) / Hoyer, S. (Autor:in) / Averell, J. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1965


    Format / Umfang :

    8 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    A close-approach solar probe design feasibility and mission study

    AVERELL, J. / HOYER, S. / LUNDHOLM, J. G. et al. | AIAA | 1965





    Solar Probe Mission Design Challenges

    Mehoke, Douglas / Potocki, Ken / Drewry, David | AIAA | 2007