Development of unsteady models for flapping wings' controller design approach

Ormancı, Filiz
Among a wide variety of micro air vehicles (MAV) due to their sizes, shapes, mechanisms and remoting technique; insect scaled flapping wing vehicles offer potential advantages like; higher agility for collision avoidance by rapid maneuvering compared to fixed wing MAVs, less noise compared to rotary wing MAVs, number of similar species in nature to imitate while modeling. Therefore, they are mainly in favor for defense applications. Main scope of the thesis is to develop an unsteady model capable of calculating aerodynamic forces and moments for insect flight. Additionally, the total forces and moments are calculated at the body center of mass by rigid body dynamics equations. By this way, during the motion of the wings, the instantaneous angle and angular acceleration of the flapping body is found. These values are used in control applications to stabilize the system. Body maneuvers are possible when right and left wings are moving with different input frequencies and amplitudes. Different cases of time dependent wing motions which are sweeping, heaving and pitching can be tested by the current analytical model. In this thesis, after analytical modelling, both a testing apparatus for analyzing only roll attitude and for analyzing all rotational body dynamics are designed. These wing systems can be used to test the model for real-time control applications.


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Çelik, Alper; Yavuz, Mehmet Metin; Department of Mechanical Engineering (2017)
Understanding and controlling the physical phenomenon behind the aerodynamics of low to moderate swept delta wings has been a challenge for researchers during the last few decades, which is stimulated by their widespread use in unmanned combat air vehicles (UCAVs) and micro air vehicles (MAVs). Although delta wings are capable of generating high lift and stable flight performance at high angle of attack, the problems related to lack of conventional flow control surfaces compel the researchers to explore new...
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Low swept delta wings, which are the simplified planforms of Unmanned Air Vehicles (UAVs), Unmanned Combat Air Vehicles (UCAVs) and Micro Air Vehicles (MAVs), have drawn considerable attention in recent years. In order to characterize and improve the operational parameters of these vehicles, the flow physics over low swept delta wings and its control should be well understood. In literature, the effect of thickness-to-chord ratio (t/C) on aerodynamic performance of a delta wing was studied on high and moder...
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Çetin, Cenk; Yavuz, Mehmet Metin; Department of Mechanical Engineering (2016)
There is an increasing interest in recent years in the aerodynamics of low swept delta wings, which can be originated from simplified planforms of Unmanned Air Vehicles (UAV), Unmanned Combat Air Vehicles (UCAV) and Micro Air Vehicles (MAV). In order to determine and to extend the operational boundaries of these vehicles with particular interest in delaying stall, complex flow structure of low swept wings and its control needs to be understood. Among different flow control strategies, blowing through differ...
Effect of wing heating on flow structure of low swept delta wing
Şencan, Gizem; Yavuz, Mehmet Metin; Güvenç Yazıcıoğlu, Almıla; Department of Mechanical Engineering (2016)
Micro Air Vehicles (MAVs), Unmanned Air Vehicles (UAVs) and Unmanned Combat Air Vehicles (UCAVs), which can be represented by simplified planforms including low swept delta wings, have many advantages in defense industry and aeronautical field. Thus, the aerodynamics of nonslender delta wings including development and application of different flow control techniques have been of considerable interest in recent years. In this study, it is aimed to investigate the effect of heating on the flow structure over...
Development of Structural Neural Network Design Tool for Buckling Behaviour of Skin-Stringer Structures Under Combined Compression and Shear Loading
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Stiffened panels are commonly used in aircraft structures in order to resist high compression and shear forces with minimum total weight. Minimization of the weight is obtained by combining the optimum design parameters. The panel length, the stringer spacing, the skin thickness, the stringer section type and the stringer dimensions are some of the critical parameters which affect the global buckling allowable of the stiffened panel. The aim of this study is to develop a design tool and carry out a geometri...
Citation Formats
F. Ormancı, “Development of unsteady models for flapping wings’ controller design approach,” M.S. - Master of Science, Middle East Technical University, 2016.