The general characteristics of multiasteroid rendezvous missions are examined, taking into account a use of an improved solar electric propulsion system, called Ion Drive. The improvements are related to the development of light-weight solar cells, extensions to high thruster power levels with high exhaust velocity, and the attachment of solar concentrators to increase the power available beyond 1.5 AU. Flight times on the order of 500-800 days are generally required. It is assumed that a stay time of about 60 days at each asteroid is adequate. Attention is given to launch and spacecraft parameters, the search technique, and multiasteroid tours involving Ceres and Vesta. It is found that at least four asteroids in the main belt, generally selected from those with known characteristics, may be reached on a single mission with a 100-kg separable probe landed on each one.


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    Titel :

    Ion Drive multi-asteroid rendezvous trajectories


    Beteiligte:
    Bender, D. F. (Autor:in)

    Kongress:

    Astrodynamics Specialist Conference


    Erscheinungsdatum :

    01.09.1977


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :






    Post-Launch Contingency Trajectories for the Near Earth Asteroid Rendezvous Mission

    McAdams, J. / American Institute of Aeronautics and Astronautics / American Astronautical Society | British Library Conference Proceedings | 1996