DC Field | Value | Language |
---|---|---|
dc.contributor.author | Won, Dae-Yeon | ko |
dc.contributor.author | Tahk, Min-Jea | ko |
dc.contributor.author | Kim, Y-H | ko |
dc.contributor.author | Kim, H. J. | ko |
dc.date.accessioned | 2013-03-12T12:26:36Z | - |
dc.date.available | 2013-03-12T12:26:36Z | - |
dc.date.created | 2012-10-11 | - |
dc.date.created | 2012-10-11 | - |
dc.date.issued | 2012-09 | - |
dc.identifier.citation | PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, v.226, no.G9, pp.1061 - 1077 | - |
dc.identifier.issn | 0954-4100 | - |
dc.identifier.uri | http://hdl.handle.net/10203/102323 | - |
dc.description.abstract | The problem of designing a robust three-axis missile autopilot that operates under aerodynamic roll angle uncertainty is addressed in this article. A finite number of local state-space models over an aerodynamic roll angle envelope are developed as a multi-model to represent uncertainty bounds. Two design methods with multi-objective output-feedback control are proposed. In the first approach, a classical three-loop autopilot structure is slightly modified for the multivariable autopilot design. The optimal gains in the autopilot structure are automatically obtained by using a co-evolutionary optimization method that addresses competing specifications and constraints. In the second approach, the mixed H-2/H-infinity performance criteria are guaranteed by multi-objective control synthesis via optimization techniques. Both design approaches are used in non-linear simulations with variations in the aerodynamic roll angle to provide satisfactory performance as a three-axis missile autopilot. | - |
dc.language | English | - |
dc.publisher | SAGE PUBLICATIONS LTD | - |
dc.subject | FLIGHT CONTROL DESIGN | - |
dc.subject | OF-ATTACK MISSILE | - |
dc.subject | CONTROL STRATEGIES | - |
dc.subject | NONLINEAR CONTROL | - |
dc.subject | OPTIMIZATION | - |
dc.subject | ROBUST | - |
dc.title | Multi-model approaches to three-axis missile autopilot design under aerodynamic roll angle uncertainty | - |
dc.type | Article | - |
dc.identifier.wosid | 000307763200002 | - |
dc.identifier.scopusid | 2-s2.0-84871731217 | - |
dc.type.rims | ART | - |
dc.citation.volume | 226 | - |
dc.citation.issue | G9 | - |
dc.citation.beginningpage | 1061 | - |
dc.citation.endingpage | 1077 | - |
dc.citation.publicationname | PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING | - |
dc.identifier.doi | 10.1177/0954410011418751 | - |
dc.contributor.localauthor | Tahk, Min-Jea | - |
dc.contributor.nonIdAuthor | Kim, Y-H | - |
dc.contributor.nonIdAuthor | Kim, H. J. | - |
dc.type.journalArticle | Article | - |
dc.subject.keywordAuthor | robust control | - |
dc.subject.keywordAuthor | three-axis missile autopilot | - |
dc.subject.keywordAuthor | multi-model approach | - |
dc.subject.keywordPlus | FLIGHT CONTROL DESIGN | - |
dc.subject.keywordPlus | OF-ATTACK MISSILE | - |
dc.subject.keywordPlus | CONTROL STRATEGIES | - |
dc.subject.keywordPlus | NONLINEAR CONTROL | - |
dc.subject.keywordPlus | OPTIMIZATION | - |
dc.subject.keywordPlus | ROBUST | - |
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