A simple suboptimal Kalman filter implementation for a gyro-corrected satellite attitude determination system
Identifieur interne : 002744 ( Istex/Corpus ); précédent : 002743; suivant : 002745A simple suboptimal Kalman filter implementation for a gyro-corrected satellite attitude determination system
Auteurs : A. De RuiterSource :
- Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering [ 0954-4100 ] ; 2010.
Abstract
This article presents a simple Kalman filter implementation for correcting gyro-determined satellite attitude estimates with attitude measurements made using external sensors such as sun sensors, magnetometers, star trackers, and so on. This article first generalizes a recently developed non-linear observer for the gyro-corrected attitude determination problem. By implementing the steady-state Kalman filter in the framework of this non-linear observer, a computationally simple filter is obtained with suboptimal steady-state performance. This is important for applications where computational power is limited, such as in micro-/nano-satellite applications. Additionally, in the absence of process and measurement noise, this implementation of the Kalman filter is globally stable. The resulting filter uses constant steady-state Kalman filter gains. It is demonstrated that close-to-optimal steady-state performance is obtained.
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DOI: 10.1243/09544100JAERO633
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De Ruiter</name><affiliation><mods:affiliation>Department of Mechanical and Aerospace, Carleton University, 1125 Colonel By Drive, Ottawa, Ontario K1S 5B6, Canada, aderuite@mae.carleton.ca</mods:affiliation></affiliation></author></analytic><monogr></monogr><series><title level="j">Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering</title><idno type="ISSN">0954-4100</idno><idno type="eISSN">2041-3025</idno><imprint><publisher>SAGE Publications</publisher><pubPlace>Sage UK: London, England</pubPlace><date type="published" when="2010">2010</date><biblScope unit="volume">224</biblScope><biblScope unit="issue">7</biblScope><biblScope unit="page" from="787">787</biblScope><biblScope unit="page" to="802">802</biblScope></imprint><idno type="ISSN">0954-4100</idno></series><idno type="istex">FC57542AE7BBAD888BD824D3218653B99CDD42BE</idno><idno type="DOI">10.1243/09544100JAERO633</idno><idno type="ArticleID">10.1243_09544100JAERO633</idno></biblStruct></sourceDesc><seriesStmt><idno type="ISSN">0954-4100</idno></seriesStmt></fileDesc><profileDesc><textClass></textClass></profileDesc></teiHeader><front><div type="abstract">This article presents a simple Kalman filter implementation for correcting gyro-determined satellite attitude estimates with attitude measurements made using external sensors such as sun sensors, magnetometers, star trackers, and so on. This article first generalizes a recently developed non-linear observer for the gyro-corrected attitude determination problem. By implementing the steady-state Kalman filter in the framework of this non-linear observer, a computationally simple filter is obtained with suboptimal steady-state performance. This is important for applications where computational power is limited, such as in micro-/nano-satellite applications. Additionally, in the absence of process and measurement noise, this implementation of the Kalman filter is globally stable. The resulting filter uses constant steady-state Kalman filter gains. It is demonstrated that close-to-optimal steady-state performance is obtained.</div></front></TEI><istex><corpusName>sage</corpusName><author><json:item><name>A de Ruiter</name><affiliations><json:string>Department of Mechanical and Aerospace, Carleton University, 1125 Colonel By Drive, Ottawa, Ontario K1S 5B6, Canada, aderuite@mae.carleton.ca</json:string></affiliations></json:item></author><subject><json:item><value>spacecraft attitude determination</value></json:item><json:item><value>computational simplicity</value></json:item><json:item><value>suboptimal filtering</value></json:item></subject><articleId><json:string>10.1243_09544100JAERO633</json:string></articleId><language><json:string>unknown</json:string></language><originalGenre><json:string>research-article</json:string></originalGenre><abstract>This article presents a simple Kalman filter implementation for correcting gyro-determined satellite attitude estimates with attitude measurements made using external sensors such as sun sensors, magnetometers, star trackers, and so on. This article first generalizes a recently developed non-linear observer for the gyro-corrected attitude determination problem. By implementing the steady-state Kalman filter in the framework of this non-linear observer, a computationally simple filter is obtained with suboptimal steady-state performance. This is important for applications where computational power is limited, such as in micro-/nano-satellite applications. Additionally, in the absence of process and measurement noise, this implementation of the Kalman filter is globally stable. The resulting filter uses constant steady-state Kalman filter gains. 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This article first generalizes a recently developed non-linear observer for the gyro-corrected attitude determination problem. By implementing the steady-state Kalman filter in the framework of this non-linear observer, a computationally simple filter is obtained with suboptimal steady-state performance. This is important for applications where computational power is limited, such as in micro-/nano-satellite applications. Additionally, in the absence of process and measurement noise, this implementation of the Kalman filter is globally stable. The resulting filter uses constant steady-state Kalman filter gains. It is demonstrated that close-to-optimal steady-state performance is obtained.</p></abstract><textClass><keywords scheme="keyword"><list><head>Keywords</head><item><term>spacecraft attitude determination</term></item><item><term>computational simplicity</term></item><item><term>suboptimal filtering</term></item></list></keywords></textClass></profileDesc><revisionDesc><change when="2010">Published</change></revisionDesc></teiHeader></istex:fulltextTEI><json:item><extension>txt</extension><original>false</original><mimetype>text/plain</mimetype><uri>https://api-v5.istex.fr/document/FC57542AE7BBAD888BD824D3218653B99CDD42BE/fulltext/txt</uri></json:item></fulltext><metadata><istex:metadataXml wicri:clean="corpus sage not found" wicri:toSee="no header"><istex:xmlDeclaration>version="1.0" encoding="UTF-8"</istex:xmlDeclaration><istex:docType PUBLIC="-//NLM//DTD Journal Publishing DTD v2.3 20070202//EN" URI="journalpublishing.dtd" name="istex:docType"></istex:docType><istex:document><article article-type="research-article"><front><journal-meta><journal-id journal-id-type="publisher-id">PIG</journal-id><journal-id journal-id-type="hwp">sppig</journal-id><journal-title>Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering</journal-title><issn pub-type="ppub">0954-4100</issn><issn pub-type="epub">2041-3025</issn><publisher><publisher-name>SAGE Publications</publisher-name><publisher-loc>Sage UK: London, England</publisher-loc></publisher></journal-meta><article-meta><article-id pub-id-type="doi">10.1243/09544100JAERO633</article-id><article-id pub-id-type="publisher-id">10.1243_09544100JAERO633</article-id><article-categories><subj-group subj-group-type="heading"><subject>Article</subject></subj-group></article-categories><title-group><article-title>A simple suboptimal Kalman filter implementation for a gyro-corrected satellite attitude determination system</article-title></title-group><contrib-group><contrib contrib-type="author"><name><surname>de Ruiter</surname><given-names>A</given-names></name><xref ref-type="aff" rid="aff1-09544100JAERO633">1</xref></contrib></contrib-group><aff id="aff1-09544100JAERO633"><label>1</label>Department of Mechanical and Aerospace, Carleton University, 1125 Colonel By Drive, Ottawa, Ontario K1S 5B6, Canada, <email xlink:href="aderuite@mae.carleton.ca">aderuite@mae.carleton.ca</email></aff><pub-date pub-type="epub-ppub"><day>1</day><month>7</month><year>2010</year></pub-date><volume>224</volume><issue>7</issue><fpage>787</fpage><lpage>802</lpage><permissions><copyright-statement>© 2010 Institution of Mechanical Engineers</copyright-statement><copyright-year>2010</copyright-year><copyright-holder content-type="other">Institution of Mechanical Engineers</copyright-holder></permissions><abstract><title>Abstract</title><p>This article presents a simple Kalman filter implementation for correcting gyro-determined satellite attitude estimates with attitude measurements made using external sensors such as sun sensors, magnetometers, star trackers, and so on. This article first generalizes a recently developed non-linear observer for the gyro-corrected attitude determination problem. By implementing the steady-state Kalman filter in the framework of this non-linear observer, a computationally simple filter is obtained with suboptimal steady-state performance. This is important for applications where computational power is limited, such as in micro-/nano-satellite applications. Additionally, in the absence of process and measurement noise, this implementation of the Kalman filter is globally stable. The resulting filter uses constant steady-state Kalman filter gains. It is demonstrated that close-to-optimal steady-state performance is obtained.</p></abstract><kwd-group><title>Keywords</title><kwd>spacecraft attitude determination</kwd><kwd>computational simplicity</kwd><kwd>suboptimal filtering</kwd></kwd-group></article-meta></front><back><ref-list><title>References</title><ref id="bibr1-09544100JAERO633"><label>1</label><citation citation-type="journal"><person-group person-group-type="author"><name><surname>Kim</surname><given-names>Y.</given-names></name> <name><surname>De Ruiter</surname><given-names>A.</given-names></name> <name><surname>Lee</surname><given-names>J.</given-names></name> <name><surname>Ng</surname><given-names>A.</given-names></name></person-group> <article-title>‘Robust implementation of Kalman filter for INS correction’</article-title> <source>Actual Problems of Aviation and Aerospace Systems: Processes, Models, Experiment</source> <volume>123</volume> (<year>2007</year>): <fpage>25</fpage></citation></ref><ref id="bibr2-09544100JAERO633"><label>2</label><citation citation-type="journal"><person-group person-group-type="author"><name><surname>Lefferts</surname><given-names>E. 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A.</given-names></name> <name><surname>Sun</surname><given-names>J.</given-names></name></person-group> <source>Robust adaptive control</source> (<publisher-loc>Upper Saddle River, New Jersey</publisher-loc>: <publisher-name>Prentice-Hall</publisher-name> <year>1995</year>)</citation></ref></ref-list></back></article></istex:document></istex:metadataXml><mods version="3.6"><titleInfo><title>A simple suboptimal Kalman filter implementation for a gyro-corrected satellite attitude determination system</title></titleInfo><titleInfo type="alternative" contentType="CDATA"><title>A simple suboptimal Kalman filter implementation for a gyro-corrected satellite attitude determination system</title></titleInfo><name type="personal"><namePart type="given">A</namePart><namePart type="family">de Ruiter</namePart><affiliation>Department of Mechanical and Aerospace, Carleton University, 1125 Colonel By Drive, Ottawa, Ontario K1S 5B6, Canada, aderuite@mae.carleton.ca</affiliation></name><typeOfResource>text</typeOfResource><genre type="research-article" displayLabel="research-article"></genre><originInfo><publisher>SAGE Publications</publisher><place><placeTerm type="text">Sage UK: London, England</placeTerm></place><dateIssued encoding="w3cdtf">2010</dateIssued><copyrightDate encoding="w3cdtf">2010</copyrightDate></originInfo><physicalDescription><internetMediaType>text/html</internetMediaType></physicalDescription><abstract>This article presents a simple Kalman filter implementation for correcting gyro-determined satellite attitude estimates with attitude measurements made using external sensors such as sun sensors, magnetometers, star trackers, and so on. This article first generalizes a recently developed non-linear observer for the gyro-corrected attitude determination problem. By implementing the steady-state Kalman filter in the framework of this non-linear observer, a computationally simple filter is obtained with suboptimal steady-state performance. This is important for applications where computational power is limited, such as in micro-/nano-satellite applications. Additionally, in the absence of process and measurement noise, this implementation of the Kalman filter is globally stable. The resulting filter uses constant steady-state Kalman filter gains. It is demonstrated that close-to-optimal steady-state performance is obtained.</abstract><subject><genre>Keywords</genre><topic>spacecraft attitude determination</topic><topic>computational simplicity</topic><topic>suboptimal filtering</topic></subject><relatedItem type="host"><titleInfo><title>Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering</title></titleInfo><genre type="journal">journal</genre><identifier type="ISSN">0954-4100</identifier><identifier type="eISSN">2041-3025</identifier><identifier type="PublisherID">PIG</identifier><identifier type="PublisherID-hwp">sppig</identifier><part><date>2010</date><detail type="volume"><caption>vol.</caption><number>224</number></detail><detail type="issue"><caption>no.</caption><number>7</number></detail><extent unit="pages"><start>787</start><end>802</end></extent></part></relatedItem><identifier type="istex">FC57542AE7BBAD888BD824D3218653B99CDD42BE</identifier><identifier type="DOI">10.1243/09544100JAERO633</identifier><identifier type="ArticleID">10.1243_09544100JAERO633</identifier><accessCondition type="use and reproduction" contentType="copyright">© 2010 Institution of Mechanical Engineers</accessCondition><recordInfo><recordContentSource>SAGE</recordContentSource><recordOrigin>Institution of Mechanical Engineers</recordOrigin></recordInfo></mods></metadata><serie></serie></istex></record>Pour manipuler ce document sous Unix (Dilib)
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