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dc.contributor.advisorChakravarthy, Animesh
dc.contributor.authorYan, Zhuo
dc.descriptionThesis (M.A.)--Wichita State University, College of Engineering, Dept. of Aerospace Engineering
dc.description.abstractIn this thesis a mathematical model of a flapping wing MAV is discussed. Aerodynamic forces and moments due to some key unsteady aerodynamic mechanisms are studied to derive the vehicle's longitudinal equations of motion under symmetric flapping assumption. The dynamic model is then simplified and linearized about a hover condition. With the assumption that the frequency of wing flapping motion is much higher than the body's natural frequency of motion, averaging theory is applied to the system. Two types of averaging methods are applied, full cycle averaging and quarter cycle averaging, to obtain a linear time invariant system (LTI) and a jump-style linear time varying (LTV) system respectively. Stability analysis and controller design are based on the linear time invariant system. A linear controller with eigenstructure assignment technique is designed and attached to the nonlinear system to stabilize the vehicle at hover condition under perturbations.
dc.format.extentviii, 85
dc.publisherWichita State University
dc.rightsCopyright 2016 by Zhuo Yan
dc.subject.lcshElectronic thesis
dc.titleModeling and control of a flapping wing micro air vehicle at hover condition

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  • AE Theses and Dissertations
    Electronic copies of theses and dissertations defended in the Department of Aerospace Engineering
  • CE Theses and Dissertations
    Doctoral and Master's theses authored by the College of Engineering graduate students
  • Master's Theses
    This collection includes Master's theses completed at the Wichita State University Graduate School (Fall 2005 -- current) as well as selected historical theses.

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