Designing An Optimal Pid Controller For Control The Plans Height, Based On Control Of Autopilot By Using Evolutionary Algorithms

Mohammad Fiuzy, Javad Haddadnia, Seyed Kamaleddin Mousavi Mashhadi
2013 Journal of Mathematics and Computer Science  
The dangers of poor pilot performance as well as time and place conditions, and such as low altitude and climate, damage critical aircraft control system. Mentioned factors, caused damage in control of sensitive military and research aircraft. So researchers had to find a solution for this problem. Therefore, the use of Unmanned Aircraft Vehicle or (UAV) in sensitive and important Operation is required. Furthermore, designing the controller system is one of the main discussed Dynamic issues in
more » ... lying Objects. Here, has been attempted to determine the optimal coefficients of PID 1 controller in Autopilot based on Optimization Algorithm such as Evolutionary Algorithms in order to regulate and desired control on height of an Unmanned Aircraft Vehicle (UAV). The proposed Cost Function simultaneously optimized the system performance specifications. Optimization done by using Evolutionary Algorithms such as GA 2 , PSO 3 and Social Policy Optimization Algorithm or ICA 4 . Finally, the system response based on Evolutionary Algorithms compared with the advantages of Classic method Optimization based on Constraints design, then you can easily decide on the superiority and being optimized of the proposed system. Aerodynamic Parameters with low precision. With this condition, designed controller shouldn't be sensitive to change of values. On the other hand, the Equations of Motion and UAV behavior is nonlinear and Varies with time. In summary, taking into account three factors is causing to complexity in the designing of Height Autopilot (controller). Three factors such as: 1 -uncertain of the Aerodynamic Coefficients (uncertainly parametric), 2 -Nonlinear Dynamics and not eliminate Coupling effects (not modeled Dynamics) and final: 3 -non-minimum height dynamics phase [1]. Several adaptive techniques have been introduced to solving the problem of uncertainly that they solve by parametric linear method [2, 3] . In [3] , an adaptive controller is used to improve the strength High Classic Controller's parameter (Resistance compared with the Aerodynamic coefficients) of an UAV. Feedback linearization [4] , is another popular technique that has many applications in designing of flight control system [5] [6] [7] [8] . So far fuzzy controllers [9] have variety applications [10-15], because it is independent of the dynamics of the system and it is able to give control commands based on system behavior. In [12] , for Autopilot, only considered uncertainly compared to Aerodynamic Coefficients. They are trying to improve the resistance parameter. In [14] a fuzzy PID Controller for linear non-minimum phase systems has been designed. In this reference, just trying to remove the Under Shot in the non-minimum phase systems. In this paper, we attempt to design an optimal PID controller, based on the optimal coefficients by the optimization algorithms that has been designed to pilot in [1], so that improve control of the height, in the introduced pilot. Firstly, for this purpose, the Mathematical Model (Dynamic) UAV will be explained, the Classic Pilot will be studied and next, we turn to description of PID controllers. Finally, the optimization algorithms, the results of simulations and discussion or conclusions will be shown.
doi:10.22436/jmcs.06.04.02 fatcat:pmuj253cnjcdjiqktkc6o343o4