A multitarget mission mode is described which utilizes the solar electric propulsion (SEP) capability to rendezvous with an asteroid after the encounter with Encke. This mode can be defined as a 'no-risk' Encke flyby mission relative to SEP technology. Launched in mid-1980, the earth-Encke transfer is all-ballistic, and SEP operation begins after comet encounter and is relied upon only to accomplish the secondary target objectives. The discussion is based on an exploratory analysis and is therefore limited in scope to a description of trajectory profile and spacecraft mass characteristics.


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    Titel :

    Comet Encke flyby - Asteroid rendezvous mission


    Beteiligte:


    Erscheinungsdatum :

    1974-04-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Comet Encke Flyby Asteroid Rendezvous Mission

    ALAN L. FRIEDLANDER | AIAA | 1974


    Comet Rendezvous Asteroid Flyby Mission

    P. Weissman / M. Neugebauer | NTIS | 1992


    The comet rendezvous asteroid flyby mission

    Weissman, Paul / Neugebauer, Marcia | NTRS | 1992


    Interplanetary mission design for the Comet Rendezvous Asteroid Flyby mission

    Williams, S. N. / Knocke, P. C. / Bright, L. E. | NTRS | 1992


    Trajectory options for the Comet Rendezvous Asteroid Flyby mission

    MILLER, S. / BENDER, D. / STETSON, D. et al. | AIAA | 1987