Features of the orbital motion control of geostationary satellites in the conditions of their collocation
Authors: Sukhoy Yu.G., Braginets V.F., Mescheryakov V.M.
Published in issue: #3(87)/2019
DOI: 10.18698/2308-6033-2019-3-1860
Category: Aviation and Rocket-Space Engineering | Chapter: Aircraft Dynamics, Ballistics, Motion Control
The article describes the analysis of features of safe orbital motion control for two geostationary satellites in one orbital zone. Under the given assumptions and limitations, the methods of controlling the satellite orbit eccentricities and inclinations by means of corrections, ensuring the implementation of the I-E-collocation method, are investigated. The result of research is the development of rational strategies for controlling the orbit eccentricities and inclinations of two satellites. The strategy of controlling eccentricity is a modification of the sun pointing perigee strategy and is called the quasi-sun pointing perigee strategy. The strategy of controlling inclinations takes into account the evolution of the orbital inclinations under the influence of the gravitational potentials of the Sun and the Moon in certain periods of the year and at different positions of the Moon orbit line of nodes. The developed strategies provide for reducing the fuel cost for the orbital parameter corrections at collocation of two satellites since eccentricity corrections are partially combined with corrections of satellite hold in longitude, and inclination corrections are performed in the most rational direction opposite to the direction of inclination vector growth
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