Browsing by Author "Arikan,K.B."

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Development of a single degree of freedom inertial measurement system
(2013) Kara,S.E.; Golmohammedzadeh,H.; Arikan,K.B.; Department of Mechatronics Engineering; 01. Atılım University
A test bench is designed to develop an inertial measurement unit. Micro electromechanical system (MEMS) type gyro and accelerometer sensors are placed on a rotating platform. Actual angular position is measured by an encoder. This paper presents design of various estimators to estimate the orientation of the test platform. Basically complementary and Kalman filter based estimators are designed and implemented on the test bench. Parameters of the estimators are optimized by using experimental data. Satisfactory results are achieved.
Disturbance Rejection Control of a Quadrotor Equipped With a 2 Dof Manupilator
(2013) Aydemir,M.; Arikan,K.B.; Irfanoǧlu,B.; Department of Mechatronics Engineering; 01. Atılım University
In this study Active Disturbance Rejection Control (ADRC) is implemented for the attitude dynamics of the quadrotor flying platform. Quadrotor model with a 2 DOF manipulator is constructed. External disturbances, manipulator dynamics and internal plant dynamics are treated as total disturbance which are estimated and rejected in simulation environment.
Citation - Scopus: 2
Experimental and Numerical Results of a Flapping Wing Four Bar Mechanism
(American Institute of Aeronautics and Astronautics Inc., 2017) Senol,M.G.; Arikan,K.B.; Kurtulus,D.F.; Department of Mechatronics Engineering; 01. Atılım University
This paper explores the design and testing of a 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 a pure flapping motion at a fixed pitch angle. Force measurements are performed for hover mode by using a force transducer. In addition, 3D numerical analyses are performed and the results are compared with the experimental measurements. Overall, CFD results show good agreement with the experimental data. © 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.