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		<label>lattes: 5801699053436537 2 SouzaSouz:2013:DESAAT</label>
		<citationkey>SouzaSouz:2013:DeSaAt</citationkey>
		<title>Design of satellite attitude control system considering the interaction between fuel slosh and flexible dynamics</title>
		<year>2013</year>
		<secondarytype>PRE CI</secondarytype>
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		<author>Souza, Alain Giacobini de,</author>
		<author>Souza, Luiz Carlos Gadelha de,</author>
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		<group>CMC-ETES-SPG-INPE-MCTI-GOV-BR</group>
		<group>DMC-ETE-INPE-MCTI-GOV-BR</group>
		<affiliation>Instituto Nacional de Pesquisas Espaciais (INPE)</affiliation>
		<affiliation>Instituto Nacional de Pesquisas Espaciais (INPE)</affiliation>
		<electronicmailaddress></electronicmailaddress>
		<electronicmailaddress>luiz.souza@inpe.br</electronicmailaddress>
		<e-mailaddress>luiz.souza@inpe.br</e-mailaddress>
		<conferencename>International Conference on Vibration Problems, 11 (ICOVP).</conferencename>
		<conferencelocation>Lisboa</conferencelocation>
		<date>2013</date>
		<publisher>IdMEC</publisher>
		<volume>1</volume>
		<pages>212-218</pages>
		<booktitle>Proceedings</booktitle>
		<tertiarytype>Paper</tertiarytype>
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		<contenttype>External Contribution</contenttype>
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		<keywords>FUEL SLOSH AND FLEXIBLE DYNAMICS, Control System Design.</keywords>
		<abstract>The design of the satellite Attitude Control System (ACS) becomes more complex when the satellite structure has different type of components like, flexible solar panels, antennas, mechanical manipulators and tanks with fuel, since the ACS performance and robustness will depend if the dynamics interaction effects between these components are considered in the satellite controller design. A crucial interaction can occur between the fuel slosh motion and the satellite rigid motion during translational and/or rotational maneuver since these interactions can change the satellite center of mass position damaging the ACS pointing accuracy. Although, a well-designed controller can suppress such disturbances quickly, the controller error pointing may be limited by the minimum time necessary to suppress such disturbances affecting thus the satellite attitude acquisition. It is known that one way to minimize such problems is to design controllers with a bandwidth below the lowest slosh and/or vibration mode which can result in slow maneuvers inconsistent with the space mission requirements. As a result, the design of the satellite controller needs to explore the limits between the conflicting requirements of performance and robustness. This paper investigates the effects of the interaction between the liquid motion (slosh) and the flexible satellite dynamics in order to predict what the damage to the controller performance and robustness is. The fuel slosh dynamics is modeled using its pendulum analogs mechanical system which parameters are identified using the Kalman filter technique. This information is used to designs and to compare the satellite attitude control system by the Linear Quadratic Gaussian (LQG) and Hinfinity methods.</abstract>
		<area>ETES</area>
		<language>en</language>
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		<notes>Setores de Atividade: Outras atividades profissionais, científicas e técnicas.</notes>
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