Distributed fixed‐time attitude coordination control for multiple rigid spacecraft
Summary In this paper, the fixed‐time attitude coordination control for multiple rigid spacecraft under an undirected communication graph is investigated. By using the backstepping technique, the distributed fixed‐time observer, and the method of “adding a power integrator,” a distributed fixed‐time...
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| Veröffentlicht in: | International journal of robust and nonlinear control 2020-01, Vol.30 (1), p.266-281 |
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| container_title | International journal of robust and nonlinear control |
| container_volume | 30 |
| creator | Zou, An‐Min Fan, Zhun |
| description | Summary
In this paper, the fixed‐time attitude coordination control for multiple rigid spacecraft under an undirected communication graph is investigated. By using the backstepping technique, the distributed fixed‐time observer, and the method of “adding a power integrator,” a distributed fixed‐time attitude coordination control law is designed for a group of spacecraft. The proposed control scheme is nonsingular and can guarantee a group of rigid spacecraft simultaneously tracking a common desired attitude within fixed time even when the time‐varying reference attitude is available only to a subset of the group members. Rigorous analysis is provided to show that the attitude consensus tracking errors can converge to the origin in finite time which is bounded by a fixed constant independent of initial conditions. Numerical simulations are carried out to demonstrate the effectiveness of the proposed control law. |
| doi_str_mv | 10.1002/rnc.4763 |
| format | Article |
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In this paper, the fixed‐time attitude coordination control for multiple rigid spacecraft under an undirected communication graph is investigated. By using the backstepping technique, the distributed fixed‐time observer, and the method of “adding a power integrator,” a distributed fixed‐time attitude coordination control law is designed for a group of spacecraft. The proposed control scheme is nonsingular and can guarantee a group of rigid spacecraft simultaneously tracking a common desired attitude within fixed time even when the time‐varying reference attitude is available only to a subset of the group members. Rigorous analysis is provided to show that the attitude consensus tracking errors can converge to the origin in finite time which is bounded by a fixed constant independent of initial conditions. Numerical simulations are carried out to demonstrate the effectiveness of the proposed control law.</description><identifier>ISSN: 1049-8923</identifier><identifier>EISSN: 1099-1239</identifier><identifier>DOI: 10.1002/rnc.4763</identifier><language>eng</language><publisher>Bognor Regis: Wiley Subscription Services, Inc</publisher><subject>adding a power integrator ; attitude coordination control ; Attitudes ; Computer simulation ; Control theory ; Coordination ; Electric power distribution ; fixed‐time control ; Initial conditions ; multiple rigid spacecraft ; Spacecraft ; Spacecraft tracking ; Tracking errors</subject><ispartof>International journal of robust and nonlinear control, 2020-01, Vol.30 (1), p.266-281</ispartof><rights>2019 John Wiley & Sons, Ltd.</rights><rights>2020 John Wiley & Sons, Ltd.</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c3303-85ab5a366e73b5e209b0486a1d096e0e234f2567a5eea02e9a4c5796e1ee545f3</citedby><cites>FETCH-LOGICAL-c3303-85ab5a366e73b5e209b0486a1d096e0e234f2567a5eea02e9a4c5796e1ee545f3</cites><orcidid>0000-0001-8504-1677</orcidid></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktopdf>$$Uhttps://onlinelibrary.wiley.com/doi/pdf/10.1002%2Frnc.4763$$EPDF$$P50$$Gwiley$$H</linktopdf><linktohtml>$$Uhttps://onlinelibrary.wiley.com/doi/full/10.1002%2Frnc.4763$$EHTML$$P50$$Gwiley$$H</linktohtml><link.rule.ids>315,781,785,1418,27926,27927,45576,45577</link.rule.ids></links><search><creatorcontrib>Zou, An‐Min</creatorcontrib><creatorcontrib>Fan, Zhun</creatorcontrib><title>Distributed fixed‐time attitude coordination control for multiple rigid spacecraft</title><title>International journal of robust and nonlinear control</title><description>Summary
In this paper, the fixed‐time attitude coordination control for multiple rigid spacecraft under an undirected communication graph is investigated. By using the backstepping technique, the distributed fixed‐time observer, and the method of “adding a power integrator,” a distributed fixed‐time attitude coordination control law is designed for a group of spacecraft. The proposed control scheme is nonsingular and can guarantee a group of rigid spacecraft simultaneously tracking a common desired attitude within fixed time even when the time‐varying reference attitude is available only to a subset of the group members. Rigorous analysis is provided to show that the attitude consensus tracking errors can converge to the origin in finite time which is bounded by a fixed constant independent of initial conditions. Numerical simulations are carried out to demonstrate the effectiveness of the proposed control law.</description><subject>adding a power integrator</subject><subject>attitude coordination control</subject><subject>Attitudes</subject><subject>Computer simulation</subject><subject>Control theory</subject><subject>Coordination</subject><subject>Electric power distribution</subject><subject>fixed‐time control</subject><subject>Initial conditions</subject><subject>multiple rigid spacecraft</subject><subject>Spacecraft</subject><subject>Spacecraft tracking</subject><subject>Tracking errors</subject><issn>1049-8923</issn><issn>1099-1239</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2020</creationdate><recordtype>article</recordtype><recordid>eNp1kM1KxDAURoMoOI6Cj1Bw46ZjfttmKaOjwqAg4zqk6a1k6DQ1SdHZ-Qg-o09ixnHr6n6X73AvHITOCZ4RjOmV782MlwU7QBOCpcwJZfJwl7nMK0nZMToJYY1x6iifoNWNDdHbeozQZK39gOb78yvaDWQ6RhvHBjLjnG9sr6N1fVr66F2Xtc5nm7GLdugg8_bVNlkYtAHjdRtP0VGruwBnf3OKXha3q_l9vny6e5hfL3PDGGZ5JXQtNCsKKFktgGJZY14VmjRYFoCBMt5SUZRaAGhMQWpuRJkqAiC4aNkUXezvDt69jRCiWrvR9-mloowSxiSvykRd7injXQgeWjV4u9F-qwhWO2cqOVM7ZwnN9-i77WD7L6eeH-e__A_2wG7-</recordid><startdate>20200110</startdate><enddate>20200110</enddate><creator>Zou, An‐Min</creator><creator>Fan, Zhun</creator><general>Wiley Subscription Services, Inc</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7SC</scope><scope>7SP</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>JQ2</scope><scope>L7M</scope><scope>L~C</scope><scope>L~D</scope><orcidid>https://orcid.org/0000-0001-8504-1677</orcidid></search><sort><creationdate>20200110</creationdate><title>Distributed fixed‐time attitude coordination control for multiple rigid spacecraft</title><author>Zou, An‐Min ; Fan, Zhun</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c3303-85ab5a366e73b5e209b0486a1d096e0e234f2567a5eea02e9a4c5796e1ee545f3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2020</creationdate><topic>adding a power integrator</topic><topic>attitude coordination control</topic><topic>Attitudes</topic><topic>Computer simulation</topic><topic>Control theory</topic><topic>Coordination</topic><topic>Electric power distribution</topic><topic>fixed‐time control</topic><topic>Initial conditions</topic><topic>multiple rigid spacecraft</topic><topic>Spacecraft</topic><topic>Spacecraft tracking</topic><topic>Tracking errors</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Zou, An‐Min</creatorcontrib><creatorcontrib>Fan, Zhun</creatorcontrib><collection>CrossRef</collection><collection>Computer and Information Systems Abstracts</collection><collection>Electronics & Communications Abstracts</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>ProQuest Computer Science Collection</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>Computer and Information Systems Abstracts Academic</collection><collection>Computer and Information Systems Abstracts Professional</collection><jtitle>International journal of robust and nonlinear control</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Zou, An‐Min</au><au>Fan, Zhun</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Distributed fixed‐time attitude coordination control for multiple rigid spacecraft</atitle><jtitle>International journal of robust and nonlinear control</jtitle><date>2020-01-10</date><risdate>2020</risdate><volume>30</volume><issue>1</issue><spage>266</spage><epage>281</epage><pages>266-281</pages><issn>1049-8923</issn><eissn>1099-1239</eissn><abstract>Summary
In this paper, the fixed‐time attitude coordination control for multiple rigid spacecraft under an undirected communication graph is investigated. By using the backstepping technique, the distributed fixed‐time observer, and the method of “adding a power integrator,” a distributed fixed‐time attitude coordination control law is designed for a group of spacecraft. The proposed control scheme is nonsingular and can guarantee a group of rigid spacecraft simultaneously tracking a common desired attitude within fixed time even when the time‐varying reference attitude is available only to a subset of the group members. Rigorous analysis is provided to show that the attitude consensus tracking errors can converge to the origin in finite time which is bounded by a fixed constant independent of initial conditions. Numerical simulations are carried out to demonstrate the effectiveness of the proposed control law.</abstract><cop>Bognor Regis</cop><pub>Wiley Subscription Services, Inc</pub><doi>10.1002/rnc.4763</doi><tpages>17</tpages><orcidid>https://orcid.org/0000-0001-8504-1677</orcidid></addata></record> |
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| issn | 1049-8923 1099-1239 |
| language | eng |
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| subjects | adding a power integrator attitude coordination control Attitudes Computer simulation Control theory Coordination Electric power distribution fixed‐time control Initial conditions multiple rigid spacecraft Spacecraft Spacecraft tracking Tracking errors |
| title | Distributed fixed‐time attitude coordination control for multiple rigid spacecraft |
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