Computer Science – Numerical Analysis
Scientific paper
Dec 1990
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1990fmet.symp..459s&link_type=abstract
In NASA, Goddard Space Flight Center, Flight Mechanics/Estimation Theory Symposium, 1990 p 459-470 (SEE N91-17073 09-13)
Computer Science
Numerical Analysis
Alignment, Apsides, Spacecraft Trajectories, Swingby Technique, Three Body Problem, Eccentricity, Encounters, Moon, Numerical Analysis
Scientific paper
The double-lunar swingby trajectory is a method for maintaining alignment of an Earth satellite's line of apsides with the Sun-Earth line. From a Keplerian point of view, successive close encounters with the Moon cause discrete, instantaneous changes in the satellite's eccentricity and semimajor axis. Numerical solutions to the planar, restricted problem of three bodies as double-lunar swingby trajectories are identified. The method of solution is described and the results compared to the Keplerian formulation.
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