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Close-approach trajectories in the elliptic restricted problem. (English) Zbl 0890.70016

From the summary: The swing-by maneuver uses a close approach with a celestial body to modify the velocity, energy, and angular momentum of a spacecraft’s orbit. The swing-by trajectories are studied and classified under the model given by the elliptic restricted three-body problem. Several simulations are made to show the effects of the eccentricity of the primaries in this maneuver. The position of the secondary in its orbit (specified by its true anomaly) also has effects on the results, and they are quantified.

MSC:

70M20 Orbital mechanics
70F07 Three-body problems
70F15 Celestial mechanics
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