<B>Orbital maneuvers between the Lagrangian points and the primaries in the Earth-Sun system</B>

Ant�nio F. B. A. Prado
2006 Journal of the Brazilian Society of Mechanical Sciences and Engineering  
This paper is concerned with trajectories to transfer a spacecraft between the Lagrangian points of the Sun-Earth system and the primaries. The Lagrangian points have important applications in astronautics, since they are equilibrium points of the equation of motion and very good candidates to locate a satellite or a space station. The planar circular restricted three-body problem in two dimensions is used as the model for the Sun-Earth system, and Lamaître regularization is used to avoid
more » ... used to avoid singularities during the numerical integration required to solve the Lambert's three-body problem. The results show families of transfer orbits, parameterized by the transfer time. , Vol. XXVIII, No. 2 / 137 minimum for a transfer to the Sun occurs for a time of flight close to 64 days, requires an energy E = -0.9999 and has a initial flight path angle of 29 deg. In terms of velocity increment (∆V) it means an impulse of 29.8 km/s (1.0001 canonical units) applied at L 1 . For a transfer to the Earth, the minimum occurs for a time of flight close to 174 days, requires an energy E = -1.4790 and has a initial flight path angle of 313 deg. In terms of velocity increment (∆V) it means an impulse of 6.1 km/s (0.2049 canonical units) applied at L 1 .
doi:10.1590/s1678-58782006000200001 fatcat:qse5dbo4orfypeptoebripuizq