Lambert problem solution in the hill model of motion |
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| Authors: | Alexander Sukhanov Antonio F Bertachini A Prado |
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| Institution: | (1) Space Research Institute (IKI), 84/32 Profsoyuznaya St., 117997 Moscow, Russia;(2) Instituto Naccional de Pesquisas Espaciais (INPE), Av. dos Astronautas, 1758 SJC |
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| Abstract: | The goal of this paper is obtaining a solution of the Lambert problem in the restricted three-body problem described by the
Hill equations. This solution is based on the use of pre determinate reference orbits of different types giving the first
guess and defining the sought-for transfer type. A mathematical procedure giving the Lambert problem solution is described.
This procedure provides step-by-step transformation of the reference orbit to the sought-for transfer orbit. Numerical examples
of the procedure application to the transfers in the Sun–Earth system are considered. These examples include transfer between
two specified positions in a given time, a periodic orbit design, a halo orbit design, halo-to-halo transfers, LEO-to-halo
transfer, analysis of a family of the halo-to-halo transfer orbits. The proposed method of the Lambert problem solution can
be used for the two-point boundary value problem solution in any model of motion if a set of typical reference orbits can
be found. |
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| Keywords: | Lambert problem three-body problem Hill equations Lagrange points halo orbit |
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