Interplanetary natural routes via Moon and Lagrangiam points L1 and L2

• Autor(a) principal: Melo, C. F. de
• Data de Publicação: 2008
• Outros Autores: MacAu, E. E. N., Winter, O. C. [UNESP]
• Tipo de documento: Artigo de conferência
• Idioma: eng
• Título da fonte: Repositório Institucional da UNESP
• Texto Completo: http://www.iafastro.net/iac/archive/browse/IAC-08/A3/2.INT/2232/; http://hdl.handle.net/11449/70792
• topic: Direct links; Earth sphere; Earth-Moon system; Equilibrium point; Heliocentric orbits; Interplanetary mission; Interplanetary trajectory; Lagrangian; Low earth orbits; Low energies; Periodic orbits; Restricted three-body problem; Small disturbances; Space explorations; Sphere of influences; Swing by; Cost reduction; Interplanetary flight; Orbits; Space research; Moon

Swing-by techniques are extensively used in interplanetary missions to minimize fuel consumption and to raise payloads of spaceships. The effectiveness of this type of maneuver has been proven since the beginning of space exploration. According to this premise, we have explored the existence of a natural and direct links between low Earth orbits and the lunar sphere of influence, to obtain low-energy interplanetary trajectories through swing-bys with the Moon and the Earth. The existence of these links are related to a family of retrograde periodic orbits around the Lagrangian equilibrium point L1 predicted for the circular, planar, restricted three-body Earth-Moon-particle problem. The trajectories in these links are sensitive to small disturbances. This enables them to be conveniently diverted reducing so the cost of the swing-by maneuver. These maneuvers allow us a gain in energy sufficient for the trajectories to escape from the Earth-Moon system and to stabilize in heliocentric orbits between the Earth and Venus or Earth and Mars. On the other hand, still within the Earth sphere of influence, and taking advantage of the sensitivity of the trajectories, is possible to design other swing-bys with the Earth or Moon. This allows the trajectories to have larger reach, until they can reach the orbit of other planets as Venus and Mars.(3σ)Broucke, R.A., Periodic Orbits in the Restricted Three-Body Problem with Earth-Moon Masses, JPL Technical Report 32-1168, 1968.