Lambert problem solution in the hill model of motion
Source: Celestial Mechanics and Dynamical Astronomy, Volume 90, Numbers 3-4, November 2004 , pp. 331-354(24)
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.
Document Type: Research Article
Affiliations: 1: Space Research Institute (IKI), 84/32 Profsoyuznaya St., 117997, Moscow, Russia, Email: firstname.lastname@example.org 2: Instituto Naccional de Pesquisas Espaciais (INPE), Av. dos Astronautas, 1758, SJC, Email: email@example.com
Publication date: November 1, 2004