DC Field | Value | Language |
---|---|---|
dc.contributor.author | Kim, Seung-Hwan | ko |
dc.contributor.author | Tahk, Min-Jea | ko |
dc.date.accessioned | 2013-03-13T02:56:37Z | - |
dc.date.available | 2013-03-13T02:56:37Z | - |
dc.date.created | 2012-10-30 | - |
dc.date.created | 2012-10-30 | - |
dc.date.issued | 2012-08 | - |
dc.identifier.citation | PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, v.226, no.G8, pp.882 - 897 | - |
dc.identifier.issn | 0954-4100 | - |
dc.identifier.uri | http://hdl.handle.net/10203/104306 | - |
dc.description.abstract | In this article, a method to make the normal acceleration of medium angle of attack missile to track some desired trajectories is presented. The dynamics which describe a missile acceleration are known to be non-minimum phase, which makes it difficult to use a straightforward feedback linearization technique. This article aims at showing that this problem may be overcome by employing cascaded regulations in the non-linear area. First, inner loop controller by dynamical sliding mode control (SMC) method based on asymptotic output tracking is designed for angle of attack control which has a minimum phase characteristics. Also then, the problem that is addressed here is the completion of the global loop by designing an additional outer loop proportional-integral (PI) controller and angle of attack estimator. The performance and stability of proposed method are illustrated via computer simulations. | - |
dc.language | English | - |
dc.publisher | SAGE PUBLICATIONS LTD | - |
dc.subject | AUTOPILOT DESIGN | - |
dc.subject | EIGENSTRUCTURE ASSIGNMENT | - |
dc.subject | SYSTEMS | - |
dc.title | Missile acceleration controller design using proportional-integral and non-linear dynamic control design method | - |
dc.type | Article | - |
dc.identifier.wosid | 000307762500001 | - |
dc.identifier.scopusid | 2-s2.0-84871784317 | - |
dc.type.rims | ART | - |
dc.citation.volume | 226 | - |
dc.citation.issue | G8 | - |
dc.citation.beginningpage | 882 | - |
dc.citation.endingpage | 897 | - |
dc.citation.publicationname | PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING | - |
dc.identifier.doi | 10.1177/0954410011417510 | - |
dc.contributor.localauthor | Tahk, Min-Jea | - |
dc.type.journalArticle | Article | - |
dc.subject.keywordAuthor | missile acceleration control | - |
dc.subject.keywordAuthor | non-minimum phase | - |
dc.subject.keywordAuthor | PI control | - |
dc.subject.keywordAuthor | dynamical SMC | - |
dc.subject.keywordAuthor | asymptotic output tracking | - |
dc.subject.keywordAuthor | angle of attack estimator | - |
dc.subject.keywordPlus | AUTOPILOT DESIGN | - |
dc.subject.keywordPlus | EIGENSTRUCTURE ASSIGNMENT | - |
dc.subject.keywordPlus | SYSTEMS | - |
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