Prado, Antonio Fernando Bertachini de Almeida Close-approach trajectories in the elliptic restricted problem. (English) Zbl 0890.70016 J. Guid. Control Dyn. 20, No. 4, 797-802 (1997). 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. Cited in 6 Documents MSC: 70M20 Orbital mechanics 70F07 Three-body problems 70F15 Celestial mechanics Keywords:effects of eccentricity of the primaries; elliptic direct orbits; elliptic retrograde orbits; hyperbolic direct orbits; hyperbolic retrograde orbits; swing-by maneuver PDFBibTeX XMLCite \textit{A. F. B. de A. Prado}, J. Guid. Control Dyn. 20, No. 4, 797--802 (1997; Zbl 0890.70016) Full Text: DOI