Synthesis, analysis and design of a novel mechanism for the trailing edge of a morphing wing

Şahin, Harun Levent
In this thesis, synthesis, analysis and design of a novel scissor-structural mechanism (SSM) with a four-bar (FB) linkage for the trailing edge of a morphing wing has been presented. The SSM, which is deployable, is created via combination of various scissor-like elements (SLEs). In order to provide mobility requirements, a FB linkage is assembled to the proposed SSM. The FB linkage is synthesized and optimized in order to give the structure required torque with a complete rotation. The SSM is designed with a novel kinematic synthesis concept in order to follow the airfoil camber with minimum design error. In this concept, various types of SLEs are assembled together to provide the desired airfoil geometries. The types (translational, polar), the number of SLEs, their orientations with respect to centerline of the airfoil and their distribution frequencies over the chord length are the design parameters, which allow designers to achieve all the possible geometric shapes. The combination rule is optimized in order to satisfy desired airfoil shapes with minimum design error as possible. Moreover, the position, velocity and acceleration analyses of the SSM have also been conducted. In order to prove aerodynamic efficiency of newly created airfoil geometries and obtain pressure distribution over the airfoil, 2D aerodynamic analyses have been done with the package program XFOIL. The flow characteristics used for the analysis are determined by the flight envelope of a generic UAV. Obtained pressure distribution is applied as the lumped force on the joints. By assigning the approximate link masses and mass centers, the dynamic force analysis of the mechanism has also been performed in order to estimate the required torque to drive the synthesized SSM.


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Tıraş, Harun; Yaman, Yaman; Department of Aerospace Engineering (2017)
In this thesis, design and analysis of a hybrid trailing edge control surface is performed. Only camber motion and twisting motion of the trailing edge control surface are considered. There are four control surface configurations that are analyzed. For the first configuration, servo actuators actuating the control surface are inside the control surface volume and control surface is without pre-twist. For the second case, the control surface is pre-twisted and actuators are inside the control surface volume....
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In this paper a detailed overview of a framework for an optimization of a morphing wing is presented. The framework presented here aids the design process of a morphing UAV wing which includes the variety of the flight phases and morphing concepts. The framework consists of two main solvers to compute the aerodynamic assessment of the wing: a fast low-fidelity module that solves the aeroelastic problem by coupling a geometrically nonlinear structural model to a potential flow aerodynamic model and a high-fi...
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This paper exploresthedesign and testing ofa flapping wing four-bar mechanism. A four-bar linkage system kinematic analysis is introduced for flapping wing motion. Four-bar mechanism is activated by a servo motor which is driven by microcontroller. The wing undergoes apure flapping motion at afixed pitchangle. Force measurements are performed for hover modeby using a force transducer. In addition, 3D numericalanalyses are performed and the results are compared with the experim...
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This thesis deals with aerodynamic optimization of morphing wings under performance and geometric constraints. In order to perform the optimization process, flow solvers computing aerodynamic lift and drag were developed as a function evaluator. A gradient based optimization method was used in order to develop the optimization algorithm. Three dimensional panel method solver was developed in order to obtain lift, pressure drag and induced drag values for a finite wing. Obtained results were compared with di...
Design and Synthesis of Aviram-Ratner-Type Dyads and Rectification Studies in Langmuir-Blodgett (LB) Films
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The design and synthesis of Aviram-Ratner-type molecular rectifiers, featuring an anilino-substituted extended tetracyanoquinodimethane (exTCNQ) acceptor, covalently linked by the sigma-spacer bicyclo[2.2.2]octane (BCO) to a tetrathiafulvalene (TTF) donor moiety, are described. The rigid BCO spacer keeps the TTF donor and exTCNQ acceptor moieties apart, as demonstrated by X-ray analysis. The photophysical properties of the TTF-BCO-exTCNQ dyads were investigated by UV/Vis and EPR spectroscopy, electrochemica...
Citation Formats
H. L. Şahin, “Synthesis, analysis and design of a novel mechanism for the trailing edge of a morphing wing,” M.S. - Master of Science, Middle East Technical University, 2018.