Aeroelastic modeling and flutter control in aircraft with low aspect ratio composite wings

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dc.contributor.authorMorris, Russell A.en
dc.contributor.committeechairMeirovitch, Leonarden
dc.contributor.committeememberHendricks, Scott L.en
dc.contributor.committeememberVanLandingham, Hugh F.en
dc.contributor.committeememberThangjitham, Suroten
dc.contributor.committeememberLibrescu, Liviuen
dc.contributor.departmentEngineering Mechanicsen
dc.date.accessioned2014-03-14T21:23:38Zen
dc.date.adate2005-12-22en
dc.date.available2014-03-14T21:23:38Zen
dc.date.issued1996en
dc.date.rdate2005-12-22en
dc.date.sdate2005-12-22en
dc.description.abstractA comprehensive study including modeling and control of aeroelastic instabilities in free flying aircraft with flexible wings has been completed. The structural model of the wing consists of a trapezoidal composite plate rigidly attached to a fuselage with rigid-body degrees of freedom. Both quasi-steady and quasi-static aerodynamic strip theories were used to analyze several different flutter mechanisms for a variety of low aspect ratio wing configurations. The most critical flutter mechanism was found to be body-freedom flutter, a coupling of aircraft pitching and wing bending motions, for wings in a forward-sweep configuration. In addition, a modal approximation to the flutter eigenvalue problem was used to substantially reduce computation cost, making the resulting model very attractive for use in larger multiobjective design packages. Composite ply angle tailoring was investigated as a passive method of increasing the body-freedom flutter airspeed of an aircraft model. In addition, wing mounted piezoelectric sensor and induced-strain actuator patches were used in conjunction with active feedback control laws to increase the airspeed at which body-freedom flutter occurs. Two control laws were tested, coupled and independent modal position feedback, to delay frequency coalescence and thus increase the flutter airspeed.en
dc.description.degreePh. D.en
dc.format.extentviii, 103 leavesen
dc.format.mediumBTDen
dc.format.mimetypeapplication/pdfen
dc.identifier.otheretd-12222005-090648en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-12222005-090648/en
dc.identifier.urihttp://hdl.handle.net/10919/40462en
dc.language.isoenen
dc.publisherVirginia Techen
dc.relation.haspartLD5655.V856_1996.M677.pdfen
dc.relation.isformatofOCLC# 36093059en
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subject.lccLD5655.V856 1996.M677en
dc.titleAeroelastic modeling and flutter control in aircraft with low aspect ratio composite wingsen
dc.typeDissertationen
dc.type.dcmitypeTexten
thesis.degree.disciplineEngineering Mechanicsen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.leveldoctoralen
thesis.degree.namePh. D.en

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