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		<secondarykey>INPE-9573-PRE/5203</secondarykey>
		<label>10980</label>
		<citationkey>GalskiOrlaKuga:2001:AuOrCo</citationkey>
		<title>Autonomous orbit control procedure, using a simplified GPS navigator, applied to the CBERS satellite</title>
		<year>2001</year>
		<secondarytype>PRE CI</secondarytype>
		<numberoffiles>1</numberoffiles>
		<size>306 KiB</size>
		<author>Galski, Roberto Luiz,</author>
		<author>Orlando, Valcir,</author>
		<author>Kuga, Hélio Koiti,</author>
		<group>DMC-INPE-MCT-BR</group>
		<conferencename>International Symposium on Space Flight Dynamics, 16.</conferencename>
		<conferencelocation>Pasadena, USA</conferencelocation>
		<date>3-7 Dec. 2001</date>
		<booktitle>Proceedings</booktitle>
		<transferableflag>1</transferableflag>
		<contenttype>External Contribution</contenttype>
		<keywords>ENGENHARIA E TECNOLOGIA ESPACIAL, CBERS 1, Autonomous Orbit Control, China-Brazil Earth Resources Satellite, GPS, Autonomous Navigator, Kalman Filter.</keywords>
		<abstract>This work presents the performance analysis of a proposed autonomous orbit control procedure, when applied to a simulation of CBERS-1, the first China-Brazil Earth Resources Satellite. A simplified GPS navigator is used in the feedback control loop, in order to supply the needed autonomous orbit information. The simplified navigator consists of a Kalman filtering process, which incorporates a procedure for automatic treatment of observation biases. The results on a long-term computer simulation (one year), which indicate the feasibility of the proposed autonomous orbit control procedure, are presented, discussed, and compared with related previous works.</abstract>
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