Flutter Optimization of a Wing-Engine System with Passive and Active Control Approaches

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dc.authoridFarsadi, Turac/0009-0002-8382-0313
dc.authoridasadi, davood/0000-0002-2066-6016
dc.contributor.authorAsadi, Davood
dc.contributor.authorFarsadi, Touraj
dc.contributor.authorKayran, Altan
dc.date.accessioned2025-01-06T17:44:54Z
dc.date.available2025-01-06T17:44:54Z
dc.date.issued2021
dc.description.abstractIn the present study, the flutter performance of a composite thin-walled beam wing-engine system is optimized by implementing two different control approaches: 1) passive open-loop and 2) active closed-loop control. Sequential quadratic programming and genetic algorithm methods are applied in the optimization process. In the passive control method, variable stiffness is acquired by constructing laminates of thin-walled beam with curvilinear fibers having prescribed paths. The goal is to exploit the desirable fiber paths with improved flutter performance to determine an optimized wing-engine aeroelastic configuration. In the active control strategy, piezo-composite actuators and the linear quadratic Gaussian algorithm are used to improve the flutter characteristics. A novel optimization strategy based on the total energy of the aeroelastic system is introduced and applied in both passive and active control strategies. The minimum total aeroelastic energy is an indication of ideal optimization variables, which leads to optimum flutter performance. The governing equations are formulated based on Librescu's thin-walled beam theory and Hamilton's principle. An unsteady aerodynamic model based on incompressible indicial aerodynamics is applied. The governing equations of motion are solved using a Ritz-based solution methodology. Numerical results demonstrate a 16 and 46% improvement in the flutter speed of the wing-engine system using the proposed passive and active control approaches, respectively. The presented results provide valuable information concerning the design of advanced lightweight and high-aspect-ratio aircraft wings with mounted engines in terms of favorable aeroelastic performance characteristics.
dc.identifier.doi10.2514/1.J059568
dc.identifier.endpage1440
dc.identifier.issn0001-1452
dc.identifier.issn1533-385X
dc.identifier.issue4
dc.identifier.scopus2-s2.0-85102424061
dc.identifier.scopusqualityQ1
dc.identifier.startpage1422
dc.identifier.urihttps://doi.org/10.2514/1.J059568
dc.identifier.urihttps://hdl.handle.net/20.500.14669/3240
dc.identifier.volume59
dc.identifier.wosWOS:000636281700025
dc.identifier.wosqualityQ2
dc.indekslendigikaynakWeb of Science
dc.indekslendigikaynakScopus
dc.language.isoen
dc.publisherAmer Inst Aeronautics Astronautics
dc.relation.ispartofAiaa Journal
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanı
dc.rightsinfo:eu-repo/semantics/closedAccess
dc.snmzKA_20241211
dc.subjectControl-Law Desıgn
dc.subjectComposıte Wıngs
dc.subjectSuppressıon
dc.subjectPlacement
dc.titleFlutter Optimization of a Wing-Engine System with Passive and Active Control Approaches
dc.typeArticle

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