Prado, Antonio Fernando Bertachini de Almeida; Broucke, Roger Transfer orbits in the Earth-Moon system using a regularized model. (English) Zbl 0888.70019 J. Guid. Control Dyn. 19, No. 4, 929-933 (1996). The authors consider the Lemaître regularization for the planar circular restricted three-body problem. In the case of the Earth-Moon system they obtain by numerical integration: orbits from the Moon back to the Moon (requiring a \(\nabla V\) under the escape velocity); orbits from the Moon to one of Lagrangian points \(L_3\), \(L_4\) or \(L_5\); orbits passing several times close to the Moon and to the Earth. These orbits are of great interest in building transportation systems and in collecting scientific data in space. Reviewer: M.-C.Anisiu (Cluj-Napoca) Cited in 10 Documents MSC: 70M20 Orbital mechanics 70F15 Celestial mechanics 70F07 Three-body problems Keywords:planar circular restricted three-body problem; Lemaitre regularization; Lagrangian points PDFBibTeX XMLCite \textit{A. F. B. de A. Prado} and \textit{R. Broucke}, J. Guid. Control Dyn. 19, No. 4, 929--933 (1996; Zbl 0888.70019) Full Text: DOI