Change of spacecraft position in a satellite system

Abstract

A system, in which satellites are located in several circular orbits with identical radius a and inclination i, but differing in longitude of ascending node Ω, is considered. The overwhelming majority of really functioning satellite systems (GLONASS, Global Positioning System (GPS), Iridium, etc.) belongs to this type. It is supposed that in one of the orbits there is a spare satellite, which should take a released place in its orbit or in orbit having another longitude of the ascending node. It is required to determine the parameters of maneuvers ensuring this transfer. This problem is sufficiently well known, therefore, the analyzed scheme of maneuvering is basically considered as a first step for developing the universal algorithm of calculation of maneuver parameters when creating satellite systems, but the obtained result can be also effectively used in order to estimate the total characteristic velocity necessary for satellite transfer to a new point. The complete description of the universal algorithm will be presented in another paper, now in press.