Dynamics and performance of tailless micro aerial vehicle with flexible articulated wings

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dc.contributor.author Paranjape, Aditya A.
dc.contributor.author Chung, Soon-Jo
dc.contributor.author Hilton, Harry H.
dc.contributor.author Chakravarthy, Animesh
dc.date.accessioned 2012-05-23T17:35:38Z
dc.date.available 2012-05-23T17:35:38Z
dc.date.issued 2012-05-05
dc.identifier.citation Paranjape A.A., Chung S.-J., Hilton H.H., and Chakravarthy A. 2012. "Dynamics and performance of tailless micro aerial vehicle with flexible articulated wings". AIAA Journal. 50 (5): 1177-1188. en_US
dc.identifier.issn 0001-1452
dc.identifier.other WOS: 000303365700016
dc.identifier.uri http://hdl.handle.net/10057/5104
dc.identifier.uri http://dx.doi.org/10.2514/1.J051447
dc.description Click on the DOI link below to access the article (may not be free). en_US
dc.description.abstract The purpose of this paper is to analyze and discuss the performance and stability of a tailless micro aerial vehicle with flexible articulated wings. The dihedral angles can be varied symmetrically on both wings to control the aircraft speed independently of the angle of attack and flight-path angle, while an asymmetric dihedral setting can be used to control yaw in the absence of a vertical tail. A nonlinear aeroelastic model is derived, and it is used to study the steady-state performance and flight stability of the micro aerial vehicle. The concept of the effective dihedral is introduced, which allows for a unified treatment of rigid and flexible wing aircraft. It also identifies the amount of elasticity that is necessary to obtain tangible performance benefits over a rigid wing. The feasibility of using axial tension to stiffen the wing is discussed, and, at least in the context of a linear model, it is shown that adding axial tension is effective but undesirable. The tu! rning performance of an micro aerial vehicle with flexible wings is compared to an otherwise identical micro aerial vehicle with rigid wings. The wing dihedral alone can be varied asymmetrically to perform rapid turns and regulate sideslip. The maximum attainable turn rate for a given elevator setting, however, does not increase unless antisymmetric wing twisting is employed. en_US
dc.language.iso en_US en_US
dc.publisher The American Institute of Aeronautics and Astronautics en_US
dc.relation.ispartofseries AIAA Journal;2012, V.50, No.5
dc.subject.classification ENGINEERING
dc.title Dynamics and performance of tailless micro aerial vehicle with flexible articulated wings en_US
dc.type Article en_US
dc.type Conference paper
dc.description.version Peer reviewed
dc.rights.holder Copyright © 2011 by the American Institute of Aeronautics and Astronautics, Inc

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