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dc.contributor.authorGraziosi, Joseph E.
dc.contributor.authorSawan, M. Edwin
dc.contributor.authorWatkins, John Michael
dc.date.accessioned2015-03-26T16:09:03Z
dc.date.available2015-03-26T16:09:03Z
dc.date.issued2014-08-03
dc.identifier.citationGraziosi, J.E.; Sawan, M.E.; Watkins, J.M., "Approximate controller design for singularly perturbed aircraft systems," Circuits and Systems (MWSCAS), 2014 IEEE 57th International Midwest Symposium on , vol., no., pp.161,164, 3-6 Aug. 2014en_US
dc.identifier.isbn978-1-4799-4132-2
dc.identifier.issn1548-3746
dc.identifier.otherWOS:000350205800041
dc.identifier.urihttp://dx.doi.org/10.1109/MWSCAS.2014.6908377
dc.identifier.urihttp://hdl.handle.net/10057/11157
dc.descriptionClick on the DOI link to access the article (may not be free).en_US
dc.description.abstractThe purpose of this paper is to extend the Quasi-Steady State Approximation and Matrix Block Diagonalization methods utilized in the Approximate Controller Design for Singularly Perturbed Aircraft Systems [1]. In that paper, it was shown that an approximate controller solution could be developed by relocating only the slow poles for two-time scale aircraft dynamics. In addition, it showed the difference between the approximate solutions and the exact solutions were bounded within limits as O(epsilon) and O(epsilon(2)). This technique was successfully applied to the lateral dynamics of the DeHaviland Canada DHC-2 Beaver.en_US
dc.language.isoen_USen_US
dc.publisherIEEEen_US
dc.relation.ispartofseries2014 IEEE 57th International Midwest Symposium on Circuits and Systems (MWSCAS);
dc.subjectAerospace controlen_US
dc.subjectAircraften_US
dc.subjectAircraft manufactureen_US
dc.subjectAircraft propulsionen_US
dc.subjectApproximation methodsen_US
dc.subjectAtmospheric modelingen_US
dc.subjectStability analysisen_US
dc.titleApproximate controller design for singularly perturbed aircraft systemsen_US
dc.typeConference paperen_US
dc.rights.holder© Copyright 2015 IEEE


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