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Transfer orbits in the Earth-Moon system using a regularized model. (English) Zbl 0888.70019

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.

MSC:

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