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| dc.contributor.author | Getachew, Mulat | |
| dc.date.accessioned | 2023-12-28T07:00:17Z | |
| dc.date.available | 2023-12-28T07:00:17Z | |
| dc.date.issued | 2022-11 | |
| dc.identifier.uri | http://ir.bdu.edu.et/handle/123456789/15556 | |
| dc.description.abstract | Aircraft is a complicated structure with numerous automated systems that must work together to provide the desired functions. Aircraft fuel tank control system is implemented to maximized the fuel system performance. The adoption and integration of a control system for an aircraft’s fuel system is a complex series of interconnected devices in the aerospace industry, that are required to supply fuel in proportion to an engine’s effective and efficient throughput. The analysis in this thesis involves calculating the fuel flow rate of a model flight cycle while taking into account all of the aircraft’s static and dynamic factors. A mathematical model of the system has been created, and the model was validated. In this Thesis, aircraft fuel tank control system is highly affected by disturbance and parameter variation. Sliding Mode Control (SMC) method was studied for controlling the fuel flow because of its robustness against model uncertainties and external disturbances. In this method, using high control gain to over come uncertainties lead to occur chattering phenomena in control law which can excite unmodeled dynamics and may harm the plant. As a result various approaches were proposed to reduce chattering. Among those intelligent methods like, Fuzzy Logic Controller (FLC) was used to reduce the sliding mode switching control law effect. Then, a sliding mode fuzzy logic controller (SMFLC) was constructed to connect with a light-wing two-engine aircraft fuel system. The proposed controller guarantees that the actual motor speed tracks the reference speed slightly faster than the proportional-integral-derivative controller. The speed difference between the actual and the reference for a PID speed controller is 0.0034 while for the SMFLC is 0.0014 which implies the PID has larger steady state error. In all cases, the proposed SMFLC controller has better performance than conventional PID controller in controlling speed of aircraft fuel tank system. SMFLC was also robust against external disturbance. The performance of the system have been simulated using the MATLAB-Simulink program. The performance of the proposed controller profile was plotted, and the extracted findings from the proposed controller was compared to similar (like PID controller) plots. Key Words: Aircraft Fuel System, Mathematical model, MATLAB-Simulink, Sliding Mode Fuzzy Logic Controller | en_US |
| dc.language.iso | en_US | en_US |
| dc.subject | Electrical and Computer Engineering | en_US |
| dc.title | Design Sliding Mode Fuzzy Logic Controller for A Twin-Engine Aircraft Fuel System | en_US |
| dc.type | Thesis | en_US |
