Pitch Aircraft Control with Type-2 FLC and PD Controller
Journal of Electrical and Electronic Engineering
Volume 3, Issue 2-1, March 2015, Pages: 12-15
Received: Nov. 7, 2014; Accepted: Nov. 10, 2014; Published: Nov. 18, 2014
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Syed Mohamad Reza Haji Mirzaie, Electrical Engineering Department, Khavaran Institute of Higher Education, Mashhad, Iran
Hodeiseh Gordan, Department of Electrical Engineering, Sobhan Institute of Higher Education, Neyshabur, Iran
Jalil Shirazi, Department of Electrical Engineering, Islamic Azad University, Gonabad Branch, Gonabad, Iran
Amin Nikbakht, Electrical Engineering Department, Khavaran Institute of Higher Education, Mashhad, Iran
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Aircraft systems are inherently unstable systems. The equations governing the motion of an aircraft are a very complicated set of six non-linear coupled differential equations. The linearized equation around the operating point is simulated in simulink MATLAB software. Also, the linear part of the system of nonlinear equations is simulated in simulink MATLAB software. In this study, combinations of PD controllers with fuzzy controller in a unity feedback system has been employed. This paper gives a comparison between the two types of FLC type-1 and type-2 in order to show the great effect of the new type of FLCs in reducing overshoot of the step response and improving the robustness of the system.
PD Controller, Pitch Aircraft Angle, Type-1 Fuzzy Logic Controller, Type-2 Fuzzy Logic Controller
To cite this article
Syed Mohamad Reza Haji Mirzaie, Hodeiseh Gordan, Jalil Shirazi, Amin Nikbakht, Pitch Aircraft Control with Type-2 FLC and PD Controller, Journal of Electrical and Electronic Engineering. Special Issue: Research and Practices in Electrical and Electronic Engineering in Developing Countries. Vol. 3, No. 2-1, 2015, pp. 12-15. doi: 10.11648/j.jeee.s.2015030201.13
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