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		<label>lattes: 1786255724025154 1 KugaCarr:2013:AtDeMa</label>
		<citationkey>KugaCarr:2013:AtDeMa</citationkey>
		<title>Attitude determination with magnetometers and accelerometers to use in satellite simulator</title>
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		<year>2013</year>
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		<author>Kuga, Helio Koiti,</author>
		<author>Carrara, Valdemir,</author>
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		<group>DMC-ETE-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>hkk@dem.inpe.br</electronicmailaddress>
		<electronicmailaddress>val@dem.inpe.br</electronicmailaddress>
		<e-mailaddress>hkk@dem.inpe.br</e-mailaddress>
		<conferencename>International Symposium on Dynamic Problems of Mechanics, 15 (DINAME).</conferencename>
		<conferencelocation>Buzios</conferencelocation>
		<date>2013</date>
		<publisher>ABCM</publisher>
		<booktitle>Proceedings</booktitle>
		<tertiarytype>Paper</tertiarytype>
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		<keywords>attitude determination, quest algorithm, satellite simulator, magnetometer, accelerometer.</keywords>
		<abstract>Systems of attitude control of artificial satellites are dependent on a reference attitude, provided by an attitude determination process. This paper presents the implementation and tests of a fully self-contained algorithm for the determination of attitude using magnetometer and accelerometer units, for application on a satellite attitude simulator based on frictionless air bearing tables. However it is known that magnetometers and accelerometers need to be calibrated so as to allow that such measurements are used to their ultimate accuracy. A calibration method is implemented which proves to be an essential part of the procedure to achieve better attitude determination accuracy. For the stepwise real time attitude determination it was used the well-known QUEST algorithm which yields quick response with reduced computer resources. The algorithms are tested and qualified with actual data collected on the streets under controlled situations. For such street runaways the experiment employs an Honeywell (solid-state magneto-resistive technology) magnetometer HMR-2300 and a Crossbow (Xbow-CD-400) IMU navigation block consisting of a triad of accelerometers and a triad of gyros, with MEMS technology. A GPS receiver is used to obtain positional information. The collected measurements are processed through the developed algorithms, and comparisons are made for attitude determination using calibrated and non-calibrated data. The results show that the implemented process of attitude determination reaches the requirements for real-time operation with enough accuracy to a regular standby or emergency mode operation.</abstract>
		<area>ETES</area>
		<language>en</language>
		<targetfile>DINAME33.pdf</targetfile>
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		<notes>Setores de Atividade: Pesquisa e desenvolvimento científico.</notes>
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