Modeling and control of a satellite’s geostationary orbit

In this Thesis a complete model of the dynamics describing the orbit of a geostationary satellite has been developed by using the Euler-Hill equations of relative motion. Following that, a system has been developed to control the satellite’s motion, which was the main objective of this work. Typically, this is classic problem in formation flight when the objective is to follow a “leader” or an analogous formation. On a similar basis, the idea developed and applied in this Thesis, was to control the satellite in order to minimize the distance from the satellite to the “leader” which in this case, is considered as a point orbiting in an ideal trajectory, irrespective of external or internal influences or disturbances. Real satellites are influenced by disturbances. Consequently, models causing those disturbances were developed. Finally, the satellite’s trajectory has been controlled using optimum and robust control design methods such as an LQ regulator and an H-infinity optimal control synthesis approach.Validerat; 20101217 (root