ROLL CONTROL FOR UAVs BY USE OF A VARIABLE SPAN MORPHING WING

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dc.contributor.advisorPines, Darryll J.en_US
dc.contributor.authorHenry, Janisa Jernarden_US
dc.contributor.departmentAerospace Engineeringen_US
dc.contributor.publisherDigital Repository at the University of Marylanden_US
dc.contributor.publisherUniversity of Maryland (College Park, Md.)en_US
dc.date.accessioned2006-02-04T08:10:44Z
dc.date.available2006-02-04T08:10:44Z
dc.date.issued2005-12-19en_US
dc.description.abstractThis thesis presents variable span wing morphing (VSWM) as an effector of roll control for unmanned aerial vehicles (UAVs). In this study, the roll coefficients obtained from VSWM are quantified by theoretical and experimental data and compared with typical aileron roll coefficients. We see that small changes in span are an effective alternative to conventional ailerons for producing roll. The standard six-degree of freedom (6-DOF) model that describes aircraft dynamics is revisited. We derive and examine the extra inertial terms that morphing introduces into the moment equations of the 6-DOF model. In this thesis, we derive simple expressions for these additional terms. In particular, we are able to extract a single degree of freedom model by considering the case of a pure roll. This model describes the dynamics of an aircraft executing a pure roll by means of span morphing. The critical distinction between the well-known aileron model and the span model derived in this thesis is clear. The span model contains an additional term whose behavior tends to modify the total damping.en_US
dc.format.extent3302441 bytes
dc.format.mimetypeapplication/pdf
dc.identifier.urihttp://hdl.handle.net/1903/3288
dc.language.isoen_US
dc.subject.pqcontrolledEngineering, Aerospaceen_US
dc.titleROLL CONTROL FOR UAVs BY USE OF A VARIABLE SPAN MORPHING WINGen_US
dc.typeThesisen_US

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