dc.contributor.author Tuzcu, Ilhan en_US dc.date.accessioned 2014-03-14T20:06:36Z dc.date.available 2014-03-14T20:06:36Z dc.date.issued 2001-12-19 en_US dc.identifier.other etd-01072002-135844 en_US dc.identifier.uri http://hdl.handle.net/10919/25958 dc.description.abstract This dissertation integrates in a single mathematical formulation the disciplines pertinent to the flight of flexible aircraft, namely, analytical dynamics, structural dynamics, aerodynamics and controls. The unified formulation is based on fundamental principles and incorporates in a natural manner both rigid body motions of the aircraft as a whole and elastic deformations of the flexible components (fuselage, wing and empennage), as well as the aerodynamic, propulsion, gravity and control forces. The aircraft motion is described in terms of three translations (forward motion, sideslip and plunge) and three rotations (roll, pitch and yaw) of a reference frame attached to the undeformed fuselage, and acting as aircraft body axes, and elastic displacements of each of the flexible components relative to corresponding body axes. The mathematical formulation consists of six ordinary differential equations for the rigid body motions and one set of ordinary differential equations for each elastic displacement. A perturbation approach permits division of the problem into a nonlinear "zero-order Problem" for the rigid body motions, corresponding to flight dynamics, and a linear "first-order problem" for the elastic deformations and perturbations in the rigid body translations and rotations, corresponding to "extended aeroelasticity." Due to computational speed advantages, the aerodynamic forces are derived by means of strip theory. The control forces for the flight dynamics problem are obtained by an "inverse" process. On the other hand, the feedback control forces for the extended aeroelasticity problem are derived by means of LQG theory. A numerical example corresponding to steady level flight and steady level turn maneuver is included. en_US dc.publisher Virginia Tech en_US dc.relation.haspart Dissertation.pdf en_US dc.rights I hereby certify that, if appropriate, I have obtained and attached hereto a written permission statement from the owner(s) of each third party copyrighted matter to be included in my thesis, dissertation, or project report, allowing distribution as specified below. I certify that the version I submitted is the same as that approved by my advisory committee. I hereby grant to Virginia Tech or its agents the non-exclusive license to archive and make accessible, under the conditions specified below, my thesis, dissertation, or project report in whole or in part in all forms of media, now or hereafter known. I retain all other ownership rights to the copyright of the thesis, dissertation or project report. I also retain the right to use in future works (such as articles or books) all or part of this thesis, dissertation, or project report. en_US dc.subject Multidisciplinary Formulation en_US dc.subject LQG Control en_US dc.subject Extended Aeroservoelasticity en_US dc.subject Perturbation Approach en_US dc.subject Flexible Aircraft Dynamics en_US dc.title Dynamics and Control of Flexible Aircraft en_US dc.type Dissertation en_US dc.contributor.department Mechanical Engineering en_US dc.description.degree Ph. D. en_US thesis.degree.name Ph. D. en_US thesis.degree.level doctoral en_US thesis.degree.grantor Virginia Polytechnic Institute and State University en_US thesis.degree.discipline Mechanical Engineering en_US dc.contributor.committeechair Meirovitch, Leonard en_US dc.contributor.committeemember Ahmadian, Mehdi en_US dc.contributor.committeemember Librescu, Liviu en_US dc.contributor.committeemember Wicks, Alfred L. en_US dc.identifier.sourceurl http://scholar.lib.vt.edu/theses/available/etd-01072002-135844/ en_US dc.contributor.committeecochair Inman, Daniel J. en_US dc.date.sdate 2002-01-07 en_US dc.date.rdate 2003-01-08 dc.date.adate 2002-01-08 en_US
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