Abstract
This study deals with solar-sail applications to geostationary satellites and the analysis of stationkeeping maneuvers. A thrust strategy for north‐south maneuvers is found as a function of the lunar inclination and the solar-sail’s characteristic acceleration. The characteristic acceleration obtained for north‐south maneuvers is used for the east‐west maneuvers thrust strategy. The dependence with respect to the Earth’s position around the sun and the sun-Earth-spacecraft relative position are analyzed for both types of maneuvers. The solar-sail stationkeeping performances are presented as a function of the geostationary satellite longitude, and the results are given for a one-year simulation. A comparison with chemical propulsion systems, from the total mass point of view, is presented. The reorbiting maneuver at the end of the operational life is also considered, and the extra propellant necessary for a chemical engine is evaluated.
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