Show simple item record

dc.contributor.authorTuzcu, Ilhanen_US
dc.date.accessioned2014-03-14T20:06:36Z
dc.date.available2014-03-14T20:06:36Z
dc.date.issued2001-12-19en_US
dc.identifier.otheretd-01072002-135844en_US
dc.identifier.urihttp://hdl.handle.net/10919/25958
dc.description.abstractThis 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.publisherVirginia Techen_US
dc.relation.haspartDissertation.pdfen_US
dc.rightsI 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.subjectMultidisciplinary Formulationen_US
dc.subjectLQG Controlen_US
dc.subjectExtended Aeroservoelasticityen_US
dc.subjectPerturbation Approachen_US
dc.subjectFlexible Aircraft Dynamicsen_US
dc.titleDynamics and Control of Flexible Aircraften_US
dc.typeDissertationen_US
dc.contributor.departmentMechanical Engineeringen_US
dc.description.degreePh. D.en_US
thesis.degree.namePh. D.en_US
thesis.degree.leveldoctoralen_US
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen_US
thesis.degree.disciplineMechanical Engineeringen_US
dc.contributor.committeechairMeirovitch, Leonarden_US
dc.contributor.committeememberAhmadian, Mehdien_US
dc.contributor.committeememberLibrescu, Liviuen_US
dc.contributor.committeememberWicks, Alfred L.en_US
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-01072002-135844/en_US
dc.contributor.committeecochairInman, Daniel J.en_US
dc.date.sdate2002-01-07en_US
dc.date.rdate2003-01-08
dc.date.adate2002-01-08en_US


Files in this item

Thumbnail

This item appears in the following Collection(s)

Show simple item record