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

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

Aug 1984

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984asdy.confq....j&link_type=abstract

American Institute of Aeronautics and Astronautics and American Astronautical Society, Astrodynamics Conference, Seattle, WA, Au

Astronomy and Astrophysics

Astronomy

Earth-Moon System, Escape, International Sun Earth Explorer 3, Orbit Calculation, Spacecraft Trajectories, Giacobini-Zinner Comet, Spacecraft Maneuvers, Swingby Technique, Trajectory Analysis, Transfer Orbits

Scientific paper

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.

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