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Control of Deflection Angle of Morphing Wing Using Fuzzy Logic System


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DOI: https://doi.org/10.15866/irease.v16i6.24344

Abstract


The morphing wing has recently received a lot of interest due to the development of smart materials and sophisticated control structures. During different phases of flight, such as take-off, cruising, and landing, the aerodynamic shape of a morphing wing can be improved. Various morphing wing structure concepts have been explored in recent years to improve flight performance. The morphing wing with a flexible leading edge, which is smooth and continuous without step or slot, is easier to construct and it promises more reliability than traditional high-lift configurations such as leading-edge slats. Significant geometric changes in an aircraft's wing during flight may enable efficient performance in disparate mission roles or enable new multi-role missions that would not be possible with a fixed-geometry aircraft. Traditional actuators and mechanisms are used in current aircraft to vary wing sweep for flight in different speed regimes, as well as to change the wing area and camber, and extend the flaps during landing and takeoff. An integrated actuator with problem detection, feedback and position control, onboard controls, and communication capabilities is called a smart actuator. This eliminates the need for external controllers and makes it simpler to install, operate, configure, and monitor the actuator. There are three different types of morphing mechanisms: airfoil morphing, in-plane morphing, and out-of-plane morphing. Each one of these categories has a different effect on aerodynamic qualities, and this project will focus on camber change and controlling it by using Intelligent Artificial then using it in model tests and ANSYS simulations.
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Keywords


Morphing Wing; Experimental Model; Control System; Fuzzy Logic; Wind Tunnel

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References


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