Abstract
The paper considers the ballistic design of spacecraft (SC) transfer to the neighborhood of the L 2 point and subsequent entry of the SC into the halo orbit. Trajectory calculations of one-impulse Earth-halo orbit transfers with and without using a lunar gravitational maneuver are presented. For the calculation of one-impulse trajectories of Earth-halo-orbit transfers, an algorithm for constructing initial approximations is applied. These approximations are constructed by calculating and analyzing the isolines as a function of two variables. This function is represented by the pericenter height of the outgoing orbit over the Earth’s surface. The arguments of the function are special parameters that characterize the halo orbit. The mentioned algorithm allows one to obtain halo orbits with specified geometrical characteristics both in the ecliptic plane, and in the plane orthogonal to it. The estimates of the characteristic velocity expenses for maintaining SC in the selected halo orbit are obtained. The described technique was used to search for working orbits of the Spectr-RG and Millimetron spacecraft. Examples of orbits obtained are presented.
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Original Russian Text © I.S. Il’in, G.S. Zaslavsky, S.M. Lavrenov, V.V. Sazonov, V.A. Stepanyantz, A.G. Tuchin, D.A. Tuchin, V.S. Yaroshevsky, 2014, published in Kosmicheskie Issledovaniya, 2014, Vol. 52, No. 6, pp. 476–488.
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Il’in, I.S., Zaslavsky, G.S., Lavrenov, S.M. et al. Ballistic design of transfer trajectories from artificial-satellite earth orbit to halo orbit in the neighborhood of the L 2 point of the Sun-Earth system. Cosmic Res 52, 437–449 (2014). https://doi.org/10.1134/S0010952514060021
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DOI: https://doi.org/10.1134/S0010952514060021