The analyses performed in altering the ISEE-3 spacecraft path from a liberation point to a helicocentric orbit for intercepting the Giacobini-Zimmer cometary tail are reviewed. The initial calculations considered the expected accuracy, the best temporal lengths to be used for the calculations and the maneuver points. The early maneuvers were also constrained to a maximum number of crossings of the terrestrial magnetotail for data collection purposes. Three earth-based tracking stations trajectory data collection schedules were projected, and programs were prepared for comparing tracking data with predictions. Delta- V maneuvers were set for perigee locations in order to conserve fuel. A 21-day span was selected for tracking, expect during maneuver periods. Accuracies of 0.1-10 km and 0.3-2.0 cm/sec were obtained.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Trajectory determination support and analysis for ISEE-3 from halo orbit to escape from the earth/moon system


    Contributors:

    Publication date :

    1984-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :