LPV modeling of a flexible wing aircraft using modal alignment and adaptive gridding methods

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dc.contributor.authorAl-Jiboory, Ali Khudhair
dc.contributor.authorZhu, Guoming
dc.contributor.authorSwei, Sean Shan-Min
dc.contributor.authorSu, Weihua
dc.contributor.authorNguyen, Nhan T.
dc.contributor.otherMichigan State University
dc.contributor.otherUniversity of Diyala
dc.contributor.otherNational Aeronautics & Space Administration (NASA)
dc.contributor.otherNASA Ames Research Center
dc.contributor.otherUniversity of Alabama Tuscaloosa
dc.date.accessioned2023-09-28T22:01:14Z
dc.date.available2023-09-28T22:01:14Z
dc.date.issued2017
dc.description.abstractOne of the earliest approaches in gain-scheduling control is the gridding based approach, in which a set of local linear time-invariant models are obtained at various gridded points corresponding to the varying parameters within the flight envelop. In order to ensure smooth and effective Linear Parameter Varying control, aligning all the flexible modes within each local model and maintaining small number of representative local models over the gridded parameter space are crucial. In addition, since the flexible structural models tend to have large dimensions, a tractable model reduction process is necessary. In this paper, the notion of sigma-shifted H-2- and H-infinity-norm are introduced and used as a metric to measure the model mismatch. A new modal alignment algorithm is developed which utilizes the defined metric for aligning all the local models over the entire gridded parameter space. Furthermore, an Adaptive Grid Step Size Determination algorithm is developed to minimize the number of local models required to represent the gridded parameter space. For model reduction, we propose to utilize the concept of Composite Modal Cost Analysis, through which the collective contribution of each flexible mode is computed and ranked. Therefore, a reduced-order model is constructed by retaining only those modes with significant contribution. The NASA Generic Transport Model operating at various flight speeds is studied for verification purpose, and the analysis and simulation results demonstrate the effectiveness of the proposed modeling approach. (C) 2017 Elsevier Masson SAS. All rights reserved.en_US
dc.format.mediumelectronic
dc.format.mimetypeapplication/pdf
dc.identifier.citationAl-Jiboory, A. K., Zhu, G., Swei, S. S.-M., Su, W., & Nguyen, N. T. (2017). LPV modeling of a flexible wing aircraft using modal alignment and adaptive gridding methods. In Aerospace Science and Technology (Vol. 66, pp. 92–102). Elsevier BV. https://doi.org/10.1016/j.ast.2017.03.009
dc.identifier.doi10.1016/j.ast.2017.03.009
dc.identifier.orcidhttps://orcid.org/0000-0003-4428-7261
dc.identifier.orcidhttps://orcid.org/0000-0002-4458-0524
dc.identifier.orcidhttps://orcid.org/0000-0002-2101-2698
dc.identifier.urihttps://ir.ua.edu/handle/123456789/12069
dc.languageEnglish
dc.language.isoen_US
dc.publisherElsevier
dc.subjectLPV modeling
dc.subjectFlexible airplane wing
dc.subjectMode alignment
dc.subjectModel reduction
dc.subjectAerospace applications
dc.subjectGAIN-SCHEDULED CONTROL
dc.subjectAEROELASTIC MODEL
dc.subjectSYSTEMS
dc.subjectCONTROLLER
dc.subjectDESIGN
dc.subjectEngineering, Aerospace
dc.titleLPV modeling of a flexible wing aircraft using modal alignment and adaptive gridding methodsen_US
dc.typeArticle
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