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Modeling and control of a satellite’s geostationary orbit
2007 (English)Independent thesis Advanced level (degree of Master (One Year)), 10 credits / 15 HE creditsStudent thesis
Abstract [en]

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.

Place, publisher, year, edition, pages
Keyword [en]
Physics Chemistry Maths, Geostationary orbit, optimum control, Extended Kalman Filter, H-infinity control synthesis, Linear Quadratic Regulator, sun-moon disturbances
Keyword [sv]
Fysik, Kemi, Matematik
URN: urn:nbn:se:ltu:diva-46737ISRN: LTU-PB-EX--07/043--SELocal ID: 45bd4130-5820-4800-867f-5d9c3482f8b3OAI: diva2:1020052
Subject / course
Student thesis, at least 15 credits
Educational program
Space Engineering, master's level
Validerat; 20101217 (root)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

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