Other
Scientific paper
Aug 1984
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984asdy.confs....d&link_type=abstract
American Institute of Aeronautics and Astronautics and American Astronautical Society, Astrodynamics Conference, Seattle, WA, Au
Other
International Sun Earth Explorer 3, Lunar Trajectories, Spacecraft Maneuvers, Swingby Technique, Trajectory Optimization, Apogees, Comets
Scientific paper
Maneuver planning procedures which permitted halving the on-board fuel consumption originally thought necessary for altering the ISEE-3 orbit from an earth-moon libration point to exploration of the terrestrial magnetotail and then on to passage through the Giacobini-Zimmer comet tail are described. The goal was to minimize the sum of delta-V maneuver components and yet meet mission and scientific requirements. Another constraint was to avoid eclipse conditions that could degrade ISEE-3 power levels and thereby thermal control capabilities, which might have destroyed the maneuvering system. The spacecraft had to stay within 6 deg of the ecliptic to assure data continuity. Swingbys of the moon were computed as needed to account for perturbations due to the earth-moon-sun system. Plane change maneuvers were found to require minimal thrust if performed at the slow-motion apogee position. The actual maneuvers for each lunar swingby are detailed.
Davis Sean A.
Dunham David W.
No associations
LandOfFree
Optimization of a multiple lunar-swingby trajectory sequence does not yet have a rating. At this time, there are no reviews or comments for this scientific paper.
If you have personal experience with Optimization of a multiple lunar-swingby trajectory sequence, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Optimization of a multiple lunar-swingby trajectory sequence will most certainly appreciate the feedback.
Profile ID: LFWR-SCP-O-1675033