Aircraft Pitch Control via Filtered Proportional-Integral-Derivative Controller Design Using Sinh Cosh Optimizer
(1) * Laith Abualigah Mail (1) Computer Science Department, Al al-Bayt University, Mafraq, 25113, Jordan. 2) Hourani Center for Applied Scientific Research, Al-Ahliyya Amman University, Amman, 19328, Jordan. 3) MEU Research Unit, Middle East University, Amman, Jordan.)
(2) Serdar Ekinci Mail (Batman University, Turkey)
(3) Davut Izci Mail (1) Department of Computer Engineering, Batman University, Batman 72100, Turkey. 2) Applied Science Research Center, Applied Science Private University, Amman, 11931, Jordan)
*corresponding author

Abstract


An innovative approach to controlling aircraft pitch is shown in this research. This approach is accomplished by adopting a proportional-integral-derivative with filter (PID-F) mechanism. A novel metaheuristic approach that we propose is called the sinh cosh optimizer (SCHO), and it is intended to further optimize the settings of the PID-F controller that is used in the aircraft pitch control (APC) configuration. An in-depth comparison and contrast of the recommended method is carried out, and statistical and time domain assessments are utilized in order to ascertain the success of the method. When it comes to managing the APC system, the SCHO-based PID-F controller delivers superior performance compared to other modern and efficient PID controllers (salp swarm based PID, Harris hawks optimization based PID, grasshopper algorithm based PID, atom search optimization based PID, sine cosine algorithm based PID, and Henry gas solubility optimization based PID) that have been published in the literature. When compared to alternative approaches of regulating the APC system, the findings demonstrate that the way that was presented is among the most successful as better statistical (minimum of 0.0033, maximum of 0.0034, average of 0.0034 and standard deviation of 5.1151E−05) and transient response (overshoot of 0%, rise time of 0.0141 s, settling time of 0.0230 s, peak time of 0.0333 s and steady-state error of 0 %) values have been achieved.

Keywords


Pitch Control of Aircrafts; Filtered PID Controller; Sinh Cosh Optimizer; Metaheuristics Algorithms

   

DOI

https://doi.org/10.31763/ijrcs.v4i2.1433 		      

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