Dynamics and Control of Morphing Aircraft

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dc.contributor.authorSeigler, Thomas Michaelen
dc.contributor.committeechairInman, Daniel J.en
dc.contributor.committeecochairSanders, Brianen
dc.contributor.committeememberRobertshaw, Harry H.en
dc.contributor.committeememberLeo, Donald J.en
dc.contributor.committeememberMason, William H.en
dc.contributor.committeememberWoolsey, Craig A.en
dc.contributor.departmentMechanical Engineeringen
dc.date.accessioned2014-03-14T20:15:18Zen
dc.date.adate2005-09-14en
dc.date.available2014-03-14T20:15:18Zen
dc.date.issued2005-08-02en
dc.date.rdate2005-09-14en
dc.date.sdate2005-08-16en
dc.description.abstractThe following work is directed towards an evaluation of aircraft that undergo structural shape change for the purpose of optimized flight and maneuvering control authority. Dynamical equations are derived for a morphing aircraft based on two primary representations; a general non-rigid model and a multi-rigid-body. A simplified model is then proposed by considering the altering structural portions to be composed of a small number of mass particles. The equations are then extended to consider atmospheric flight representations where the longitudinal and lateral equations are derived. Two aspects of morphing control are considered. The first is a regulation problem in which it is desired to maintain stability in the presence of large changes in both aerodynamic and inertial properties. From a baseline aircraft model various wing planform designs were constructed using Datcom to determine the required aerodynamic contributions. Based on nonlinear numerical evaluations adequate stabilization control was demonstrated using a robust linear control design. In maneuvering, divergent characteristics were observed at high structural transition rates. The second aspect considered is the use of structural changes for improved flight performance. A variable span aircraft is then considered in which asymmetric wing extension is used to effect the rolling moment. An evaluation of the variable span aircraft is performed in the context of bank-to-turn guidance in which an input-output control law is implemented.en
dc.description.degreePh. D.en
dc.identifier.otheretd-08162005-134143en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-08162005-134143/en
dc.identifier.urihttp://hdl.handle.net/10919/28681en
dc.publisherVirginia Techen
dc.relation.haspartSeigler05_Dissertation.pdfen
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subjectFlight Dynamicsen
dc.subjectFlight Controlen
dc.subjectMorphing Aircraften
dc.titleDynamics and Control of Morphing Aircraften
dc.typeDissertationen
thesis.degree.disciplineMechanical Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.leveldoctoralen
thesis.degree.namePh. D.en

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