Alternative gravity-assist sequences for the ISEE-3 escape trajectory

Details Alternative gravity-assist sequences for the ISEE-3 escape trajectory Alternative gravity-assist sequences for the ISEE-3 escape trajectory

Aug 1984

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

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

Statistics

Methodology

International Sun Earth Explorer 3, Lunar Trajectories, Orbital Maneuvers, Solar Gravitation, Swingby Technique, Transfer Orbits, Angular Momentum, Apogees, Comets

Scientific paper

The International Sun-Earth Explorer-3 (ISEE-3) was moved from its mission halo orbit upstream of the earth's magnetosphere on June 10, 1982. Multiple lunar swingby maneuvers were then used to shape the trajectory for extensive exploration of the distant geomagnetic tail and finally to place the spacecraft on a course that will intercept the comet Giacobini-Zinner on September 11, 1985. With this new mission objective, the spacecraft was renamed the International Cometary Explorer (ICE). A double-lunar-swingby control technique involving five passes by the moon was eventually implemented to accomplish this, but in the process of finding this solution several feasible, though less optimal, alternative trajectory sequences implementing the same procedure were discovered. This paper provides a descriptive comparison of these very different orbital profiles and serves to illustrate the utility and great flexibility of this orbital control procedure. Targeting methodology for finding constrained solutions in this space is also presented.

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