Title:
A Combined Piezoelectric Composite Actuator and Its Application to Wing/Blade Tips

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dc.contributor.advisor Dancila, D. Stefan
dc.contributor.author Ha, Kwangtae en_US
dc.contributor.committeeMember Lynch, Christopher S.
dc.contributor.committeeMember Armanios, Erian A.
dc.contributor.committeeMember Ruzzene, Massimo
dc.contributor.committeeMember Bauchau, Olivier A.
dc.contributor.department Aerospace Engineering en_US
dc.date.accessioned 2006-01-18T22:25:17Z
dc.date.available 2006-01-18T22:25:17Z
dc.date.issued 2005-11-28 en_US
dc.description.abstract A novel combined piezoelectric-composite actuator configuration is proposed and analytically modeled in this work. The actuator is a low complexity, active compliant mechanism obtained by coupling a modified star cross sectional configuration composite beam with a helicoidal bimorph piezoelectric actuator coiled around it. This novel actuator is a good candidate as a hinge tension-torsion bar actuator for a helicopter rotor blade flap or blade tip and mirror rotational positioning. In the wing tip case, the tip deflection angle is different only according to the aerodynamic moment depending on the hinge position of the actuator along the chord and applied voltage because there is no centrifugal force. For an active blade tip subject to incompressible flow and 2D quasi steady airloads, its twist angle is related not only to aerodynamic moment and applied voltage but also to coupling terms, such as the trapeze effect and the tennis racquet effect. Results show the benefit of hinge position aft of the aerodynamic center, such that the blade tip response is amplified by airloads. Contrary to this effect, results also show that the centrifugal effects and inertial effect cause an amplitude reduction in the response. Summation of these effects determines the overall blade tip response. The results for a certain hinge position of Xh=1.5% chord aft of the quarter chord point proves that the tip deflection target design range[-2,+2] can be achieved for all pitch angle configurations chosen. en_US
dc.description.degree Ph.D. en_US
dc.format.extent 1756591 bytes
dc.format.mimetype application/pdf
dc.identifier.uri http://hdl.handle.net/1853/7575
dc.language.iso en_US
dc.publisher Georgia Institute of Technology en_US
dc.subject Blade tip en_US
dc.subject Coiled bender actuator
dc.subject Tension-torsion bar
dc.subject Piezoelectric actuator
dc.subject Starbeam
dc.subject.lcsh Composite materials Design and construction en_US
dc.subject.lcsh Piezoelectric devices en_US
dc.subject.lcsh Actuators en_US
dc.subject.lcsh Airplanes Wings Design and construction en_US
dc.title A Combined Piezoelectric Composite Actuator and Its Application to Wing/Blade Tips en_US
dc.type Text
dc.type.genre Dissertation
dspace.entity.type Publication
local.contributor.corporatename College of Engineering
local.contributor.corporatename Daniel Guggenheim School of Aerospace Engineering
local.relation.ispartofseries Doctor of Philosophy with a Major in Aerospace Engineering
relation.isOrgUnitOfPublication 7c022d60-21d5-497c-b552-95e489a06569
relation.isOrgUnitOfPublication a348b767-ea7e-4789-af1f-1f1d5925fb65
relation.isSeriesOfPublication f6a932db-1cde-43b5-bcab-bf573da55ed6
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