ISEE-3 trajectory control utilizing multiple lunar swingbys

Details ISEE-3 trajectory control utilizing multiple lunar swingbys ISEE-3 trajectory control utilizing multiple lunar swingbys

Aug 1984

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

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

Astronomy and Astrophysics

Astronomy

International Sun Earth Explorer 3, Spacecraft Maneuvers, Swingby Technique, Trajectory Control, Hydrazine Engines, Lunar Gravitation, Mission Planning, Trajectory Optimization

Scientific paper

The International Sun-Earth Explorer-3 (ISEE-3) extended mission maneuvers required to control lunar swingby trajectories presented a unique targeting problem that could not be solved analytically. A procedure consisting of nested sensitivity studies was therefore developed. This paper presents this control procedure as adapted to the ISEE-3 spacecraft and mission profile. Maneuver planning, execution, and evaluation techniques implemented for trajectory control are described. An example is presented showing how lunar targeting distances were achieved. The results of analysis using this procedure are shown in a maneuver summary. The continued use of this procedure allowed accurate control of the final lunar swingby.

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